HANDBOOK OF LEAFLET DISPERSION VIA BALLOONS

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP78-03639A000500080001-1
• Release Decision: RIPPUB
• Original Classification: C
• Document Page Count: 156
• Document Creation Date: December 22, 2016
• Document Release Date: May 3, 2011
• Sequence Number: 1
• Publication Date: March 1, 1959
• Content Type: REPORT

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HANDBOOK OF
LEAFLET DISPERSION
VIA BALLOONS
rn
tl
AV
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Page
Characteristics of Leaflet Descent and Dispersion
Tables
Making the Computation
Leaflet Descent - 1
8 to 31
32
J-100 Balloon Delivery System
Operating Instructions
J-100-1
J-100-43
170F Balloon Delivery System
170F-1
J-9-10-300 Balloon Delivery System
J-300-1
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This handbook describes the process of delivering leaflets to
specified target areas via balloons. It covers the technical aspects of
sending up balloons from different types of launching sites, the calcu-
lations which must be made to deliver the payload to its destination and
dispersal in a desired pattern. A section is included which describes
the characteristics of leaflet descent and dispersion. The effects of
long and short range drift, and considerations of altitude and weather
conditions as they apply to the various balloon delivery systems are
detailed along with instrument checkout and launching instructions.
Meterology - Given detailed knowledge of the winds and air currents,
controlled leaflet coverage of a target is entirely feasible by carefully
selecting the balloon and leaflet load variables which are under the
control of the operating personnel. Without such knowledge of the air
currents, any attempt at controlled leaflet coverage is entirely in
vain. For the purposes of this handbook it is assumed that adequate
knowledge of the winds will be provided for use of the operating per-
sonnel whose job it is to select the appropriate balloon and leaflet
characteristics to attain the desired leafleting dispersal pattern at
the target destination.
A detailed discussion of meteorological problems is beyond
the scope of this handbook, but there are certain basic meteorological
factors which must be recognized in order to successfully launch leaf-
let dispensing balloons.
To begin with, a weather study of the wind pattern from the pro-
posed launching area into the intended target area must be made. Since
balloons are carried aloft and borne to destination by winds and air
currents, a strong steady air stream in the correct direction is the
most desirable and reliable form of transportation for predictable re-
sults. An illustration of such an ideal air stream is seen in the pre-
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vailing westerly winds generally found in the middle latitudes at heights
varying from a few thousand feet above the ground to the beginning of
the stratosphere.
If the weather study indicates that a favorable percentage of
launching winds may be expected, then the problem of forecasting the
weather arises. Here, the services of a qualified meteorologist who is
familiar with the requirements of the operation are an absolute must!
The meteorologist with his knowledge of local meteorological conditions,
will prepare weather maps that enable him to make preliminary long
range forecasts. The long range forecasts alert the operation to any
approaching opportunities for launching balloons. Arrangements also
should be made with as many radiosonde stations as possible to obtain
their data promptly. With this information the progress of developing
wind patterns can be monitored, and preliminary trajectories can be
worked up.
Finally, if the weather situation develops as predicted, the
winds at the launching site should be verified with a theodolite.
Three Ranges of Delivery - The technical considerations involved in
delivering leaflets by balloon differ according to the distance to be
traversed to reach the target. This necessitates treatment of the
problems in three categories:
1. Short range leafleting operations (under Z50 miles)
2. Mid range leafleting operations (250 to 600 miles)
3. Long range leafleting operations (up to 1500 miles)
It should be noted that the type of wind information needed and the
amount of control attempted over the balloon and leaflets is not at all
the same for each of these three different leafleting operations.
For the short range leafleting effort, a detailed study of the
winds over a comparatively brief time interval is sufficient. In con-
trast, the problem of long range penetration requires forecasting
the characteristics of general weather movement over an adequately
longer span of time. In addition, the variations inherent in windflow
limit the effectiveness of the controls which can be exercised to direct
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a leaflet balloon over long distances. The mid range effort requires
weather observations over a period of time that falls somewhere in
between the times for short and long range observations.
Impact and Dispersal - The "rule of thumb" for leaflet dispersion is
that actual impact may vary from the predicted impact by as much as
10 percent of the distance the balloon travels. This means that for a
short range target of 150 miles, the center of impact could be as much
as 15 miles away from the predicted center of impact. However, this
does not necessarily mean failure of the attempt because the dimen-
sions of the leaflet pattern itself generally will be large enough to as-
sure substantial coverage of the chosen target. It therefore follows
that the efforts made to control the rise and burst of the balloon are
fully warranted in short range leafleting.
Applying the same rule to mid range leafleting; a target 400
miles distant might have a center of impact as much as 40 miles away
from the target area (and it also could be nearer than this to the tar-
get) so here again an effort at control is warranted.
The long range target 1000 miles distant presents quite a differ-
ent problem. In this case an error of 10 percent amounts to 100 miles,
thus it is impractical to attempt to leaflet any but a very general area.
The Systems - In this handbook the balloon systems for leaflet disper-
sion will be described with differing emphasis in accordance with each
system's range capability and technical aspects.
The J-100 balloon, a short range system, will be described
with intensive treatment of its performance characteristics under vari-
ous conditions of load and free lift. Only brief attention will be given
to the rigging and launching of this relatively simple balloon system.
In connection with this J-100 system the section on "Characteristics of
Leaflet Descent and Dispersion" should receive careful study since
those characteristics are most important for short range leafleting
and impact predictions. Also, these characteristics should be well
understood for profitable application to the longer range problems.
The Pillow balloon constitutes a mid range capability (250 to
600 miles) where control of the payload can be used to select the de-
sired floating level, but where free lift control is ineffective. The
basic mechanism is somewhat more involved in this case, consequently
this aspect will receive greater emphasis.
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The 170 and 180 balloons are long range systems, and no con-
trol through varying either the load or free lift will be attempted here.
Instead, detailed instrument check out and launching instructions will
be given for these more sophisticated systems.
IV
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Characteristics of Leaflet
Descent and Dispersion
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TARGET COVERAGE
BASIC LEAFLET DESCENT
IMPACT PATTERN
GENERAL LEAFLET TABLES
Page
TABLE G-1 Length-Aspect Combinations
8
G-2 Leaflets per Pound
9
G-3 Ground Level Descent Rates
10
G-4 Variation Co-efficients
11
G-5 Ground Patterns
12
A-1 Descent Times (Autorotators)
13
A-2 Time Factors - 5000 Ft. Increments
(Autorotators)
15
A-3 Time Factors - Standard Wind
(Autorotators)
17
A-4 Descent Rates (ft/sec) (Autorotators)
20
NA-1 Descent Times (Non-autorotators)
22
NA-2 Time Factors - 5000 Ft. Increments
(Non-autorotators)
24
NA-3 Time Factors - Standard Wind
(Non-autorotators)
26
NA-4 Descent Rates (ft/sec) (Non-autorotators)
30
MAKING THE COMPUTATIONS
32
Example of Computations No. 1
32
Example of Computations No. 2
35
Example of Computations No. 3
37
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LEAFLET DESCENT
CHARACTERISTICS OF LEAFLET DESCENT AND DISPERSION
Abstract - In order to blanket a target area with leaflets they must be
released at a point in space where they will disperse and descend in a
predictable pattern. To attain this objective there are two requisites:
1. A transport delivery system to the point of release.
2. A knowledge of leaflet descent and dispersion characteris-
tics, and their calculation.
This section analyzes the behavior of leaflets when released in
space and the factors which influence them in their descent to the
ground. In this section there is a description of the types of motion
assumed by leaflets when descending, and how the type of motion influ-
ences the rate of descent and dispersal. Wind drift at different altitude
increments, and resulting ground patterns are discussed. Changing the
rate of fall and dispersion of leaflets by varying the size and weight of
paper is explained with a view to aid in the selection of leaflets.
The fundamental principles of leaflet descent and dispersion dis-
cussed here include the basic mathematical equations and computations
for a full understanding of their derivation. However, a full set of
tables is included for ready reference to obviate the necessity of mak-
ing extensive calculations in the field.
Following the tables there are a number of examples to illus-
trate the method of computing release points, drift, ground coverage
patterns and density of coverage with coefficients of variation.
A thorough understanding of the characteristics of leaflet de-
scent and dispersion covered in this section is a must for short range
leafleting operations. It is an invaluable background for making the
computations and predictions necessary to successful leafleting at any
range of operation.
Target Coverage - Calculation of leaflet descent and dispersion patterns
depends on a knowledge of wind speed and direction within each 5000-
foot increment of altitude, and a knowledge of leaflet descent character-
istics and rate of fall within each increment.
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LEAFLET DESCENT
Given data on these factors, a horizontal leaflet pattern can be
worked back in space from the target. The pattern will be a series of
vectors* such as shown here. Viewpoint is from above looking towards
the ground, at 5000-foot intervals.
Obviously, release of the leaflets at any point on these vectors
could result in target coverage. But the important consideration here
is the characteristics of the leaflets when released in free fall. What
general rules of behavior do they obey; does the action of selected leaf-
lets differ; hoW can their motion be computed; can ground patterns be
predicted?
Basic Leaflet Descent - A basic difference between falling leaflets is
the type of motion they assume during descent. This can be one of two
forms: an autorotating motion or a non-autorotating motion. An auto-
rotating leaflet is one which exhibits a very stable fall with the leaflet
rotating about its longest axis.
* The term vector is applied to quantities which have both direction
and magnitude. Any vector quantity may be represented by an arrow
drawn in the appropriate direction and having a scaled length which
depicts the numerical value of the quantity.
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The other types of fall (flip-flop, spiraling, etc.) can be grouped
together for purposes of analysis. In general, these have a somewhat
more rapid and less stable type of descent than the autorotators.
Empirical descent rate equations have been derived for each of
these two general forms of motion:
Autorotation V = Vo (I - 0.051 H) I/3 eo- 105H
V = V60-0.051H ) 213 g 0.0525H 2
where V = descent rate at any height H (in ft/sec)
V,= ground rate of descent (in ft/sec)
H = altitude (in feet)
Knowing the type of motion which any particular leaflet assumes
and having measured its ground rate of descent (Vo), it is now possible
to calculate the rate of descent (V) at any altitude (H) by simply plugging
the values of Vo and H into the appropriate equation and solving. The
more important use of the descent rate equation, however, is in calcu-
lating the time down. This can be obtained by performing an integration
of the integral: 2
T = I/V dH
The tables included in this handbook make it unnecessary for the
operator to perform the integration himself; the method has been out-
lined to show the basic calculations.
Knowing the time spent within successive increments of altitude,
and having the wind velocity and direction for these same altitude incre-
ments, it is simply a process of plotting vectors in order to determine
the leaflet drift from release to impact.
One further measure of basic leaflet fall is necessary in order
to determine dispersal. This is the coefficient of variation, which is
the ratio of the descent time for 90% of the leaflets to the average de-
scent time, which is designated by the symbol RT/ To . This coefficient
can be obtained at the same time the ground rate of descent (Vo) meas-
urements are made. A high coefficient (anything above 0. 50) means
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LEAFLET DESCENT
that there is a considerable variation in the rate at which the leaflets
fall, while a low coefficient (below 0. 50) means that the leaflets tend
to fall much at the same rate.
Impact Pattern - Having plotted the drift vectors and knowing the
variation coefficient for the particular leaflets of interest, it is now
possible to calculate the size of the impact area for a single-point
release.
An elliptical ground pattern results from a single-point re-
lease, the long or major axis of the ellipse being along the resultant
drift vector S and the minor axis being normal to it. Not only is
the major axis directed along the horizontal drift vector, but it is
proportional to it also, the proportionality factor being the variation
coefficient RT/Ta . The relationship of the difference of drift to the
total drift from release to center of impact is:
O S = (RT/To) S-r
This constitutes the major contribution to the major axis. To this
should be added one-half the release altitude for the leaflets, which is
about the amount of natural dispersion for leaflets in still air. However,
the latter is usually a minor factor.
The minor axis of the ellipse is the sum of the natural disper-
sion (one-half the release altitude) and the product of the coefficient of
variation times the net maximum distance N -that the vector incre-
ments deviate in the normal from the horizontal drift vector. That is:
= 1 /2 H + (RT/To) N
The overall picture can be described then as:
major axis
A -S = (RT/To) S'
= I/2 H +(RT/TT)N
GROUND PATTERN
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Knowing the major and minor axes of the ellipse which includes
90 percent of the leaflets released, permits calculation of the average
density. The area of the ellipse is given by the formula A= 4 ab where
a and b are the major and minor axes. Dividing the number of leaflets
released by this area figure, and multiplying the result by 0.90 (since
the area includes only 90 percent of the leaflets) yields the average den-
sity. The factor 0. 90 can be ignored without serious error, however,
in which case the average density is simply the number of leaflets re-
leased divided by the area of the ground pattern.
To summarize, the following information is needed in order to
determine the wind drift and ground pattern of any given type of leaflet.
1. A breakdown of the wind by velocity and direction for each
5000-foot increment of altitude through which the leaflet
will fall.
2. The release height.
3. Class of leaflet: autorotator or non-autorotator.
4. The ground rate of descent (V0).
5. The variation coefficient ( RT/To ) .
Performance Tables - A computation form sheet plus a series of leaflet
performance tables and illustrative examples follow. Adopting a stan-
dard approach to working up the leaflet descent and dispersion informa-
tion will save considerable time for the operator. The technique pro-
posed need not be followed rigorously; but, it is a useful one and is
recommended until the operator develops considerable familiarity with
the tables and the problem solving process.
General Leaflet Tables - The leaflet performance tables are described
below. The first set of tables are General Leaflet Tables (or "G"
Tables).
Table G-1 - Width and Areas of Leaflets with Different Length-
Aspect Ratio Combinations.
As a convenience in presenting data on leaflets in some of the
succeeding tables, leaflet sizes are identified by length and aspect
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ratio, the aspect ratio being the ratio of the length to the width. The
width and area of these different length-aspect ratio combinations are
presented in Table G-1. The operator can therefore readily select the
size of leaflet that he would like to work with from this table and then
procede to identify it by its appropriate length-aspect ratio designation
for the remainder of his computations.
Table G-2 - Leaflets per Pound
In planning leaflet operations, it is necessary to know the num-
ber of leaflets per pound. The number of leaflets per pound for 40 dif-
ferent leaflet sizes in 4 different paper weights are listed in this table.
It should be recalled that the paper weight is the weight of 2000 leaflets
of 8-1/2 x 11 inch size, and that the number of leaflets per pound can
be calculated from the formula:
2000 x 11" x 8-1/2"
No. of leaflets/lb. = Paper length x paper width x paper weight
Table G-3 - Ground Level Descent Rates
Having selected the paper size and weight to work with, it is now
necessary to establish whether the leaflet is an autorotator or non-
autorotator, and its ground level rate of descent. The ground rates of
descent are listed in this table with the underlined values designating
those leaflets which are autorotators,
Table G-4 - Variation Coefficients ( RT/To )
The variation coefficient which is used to calculate the leaflet
dispersion is listed here for each leaflet size and weight.
Table G-5 - Ground Pattern Areas
This table is provided as a convenience in computing ground
pattern areas. It is assumed that the patterns are elliptical, and, if a
and b are the major and minor axes, then the area is
A= -Mob
where 7r is 3. 14. It is almost as easy to perform the multiplication
itself as it is to refer to the tables, but they are included for conven-
ience.
-6-
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Descent Data - The following tables provide descent data on the autoro-
tating and non-auto rotating leaflets. The autorotating tables are de-
signated as "A" Tables. The non-autorotating tables are designated as
"NA" Tables.
Tables A-1 and NA-1 - Total Descent Times (hours)
Values in these tables present the total descent times for leaflets
with various Vo values and release heights for each of the two classes
of leaflets. They are listed for use in planning leaflet operations.
Tables A-2 and NA-L - Time Factors (hours) for the Descent of
Leaflets through 5000-foot Increments
These tables present times in hours that autorotating and non-
autorotating leaflets with different ground descent rates remain within
5000-foot height intervals. The tables are most commonly utilized for
computing vectorially the leaflet drift from release to impact.
Tables A-3 and NA-3 - Time Factors (hours) for the Descent of
Leaflets to be Used with Standard Wind Data
Time factors in these tables are designed for direct use with
wind measurements which have been transmitted in the standard form
from a meteorological observing station. Plotting the horizontal drift
vector using this method, as compared to that for 5000-foot incre-
ments, may be somewhat more laborious, but the individual operator
can decide this.
Tables A-4 and NA-4 - Descent Rates at Different Altitudes
These values do not enter directly into any of the computations
but are included as a source of information where needed in planning
operations.
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WIDTH AND AREAS OF LEAFLETS WITH
DIFFERENT LENGTH-ASPECT RATIO COMBINATIONS
Aspect Ratio
Paper
Length
1.00
1 25
1.50
1 75
2.00
2 50
2 75
3000
3 25
4.00
4"
Width
(in.) 4.00
3.20
2.67
2.29
2.00
1.60
1.45
1.33
1.23
1.00
Area
(in.2) 16.00
12.80
10.70
9.20
8.00
6.40
5.80
5.30
4.90
4.00
6"
Width
(in.) 6.00
4.80
4.00
3.43
3.00
2.40
2.18
2.00
1.85
1.50
Area
(in.2) 36.00
28.80
24.00
20.60
18.00
14.40
13.10
12.00
11.10
9.00
411
Width
(in.) 8.50
6.39*
5.67
4.86
4.25
3.40
3.09
2.83
2.62
2.13
Area
(in.2) 72.30
54.30
48.20
41.30
36.10
28.90
26.30
24.10
22.30
18.10
11"
Width
(in.) 11.00
8.80
7.33
6.29
5.50
4.40
4.00
3.67
3.38
2.75
Area
(in.2) 12L 00
96.80
80.60
69.20
60.50
48.40
44.00
40.40
37.20
30.30
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Aspect Ratio (Ratio of Length to Width)
Paper
Weight
Paper
Length
1.00
1.25
1.50
1.75
2.00
2.50
2.75
3.00
3.25
4.00
9 lb
4"
1299
1623
1948
2273
2597
3247
3571
3896
4220
5194
6"
577
721
866
1010
1154
1443
1587
1731
1876
2309
8j"
288
382*
431
503
575
719
791
863
935
1150
11"
172
215
258
301
343
429
472
515
558
687
13 lb
4"
899
1124
1349
1573
1798
2248
2472
2697
2922
3596
6"
400
499
599
699
799
999
1099
1199
1299
1598
8-21"
199
265*
299
348
398
498
548
597
647
796
11"
119
149
178
208
238
297
327
357
386
476
16 lb
4"
730
913
1096
1278
1461
1826
2009
2191
2374
2922
6"
325
406
487
568
649
812
893
974
1055
1299
82"
162
215*
243
283
324
404
445
485
526
647
11"
97
121
145
169
193
241
266
290
314
386
20 lb
4"
584
730
877
1023
1169
1461
1607
1753
1899
2338
6"
260
325
390
455
519
649
714
779
844
1039
82"
129
172*
194
226
259
324
356
388
421
51.8
11"
77
97
116
135
1.55
193
212
232
251
309
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TABLE G-3
GROUND LEVEL DESCENT RATES
(Vo, ft/sec)
Aspect Ratio (Ratio of Length to Width)
Paper
Weight
Paper
Length
1.00
1.25
1.50
1.75
2.00
2.50
2.75
300
3.25
4.00
9 lb
4"
2.0
2.2
2.2
2.2
2.1
1_3*-*
1.0
1_3
1_3
1_3
6"
2.4
2.2
2.3
2.6
3.1
2.5
2.6
2.3
2.2
1.8
8&"
2.9
2.1*
2.2
2.4
2.7
3.0
3.0
2.0
2.9
11"
2.5
2.6
2.6
2.5
2.9
2.8
2.8
2.8
2.6
2.5
13 lb
4"
2.2
2.4
2.6
2.6
1.8
1.3
1.3
1.33
1_5
1.6
6"
2.3
2.4
2.7
2.9
3.6
2.4
1.5
1-3
1.5
1_5
8j"
2.5
2.2*
3.0
2.8
3.4
3.4
3.2
2.3
2.9
2.0
11"
3.1
2.6
2.8
2.7
3.0
3.5
3.6
3.0
2.9
2.1
16 lb
4"
2.4
2.6
2.8
2.3
1.5
1.4
1.5
1.5
1.6
1.9
6"
2.7
2.8
3.3
4.5
4.7
1.4
1.4
1.6
1.9
2.1
8j"
2.7
2.6*
3.2
3.4
3.8
4.4
3.6
1.8
2.2
1.8
11"
3.3
2.8
3.0
2.7
4.5
4.1
3.9
4.0
2.9
1.7
20 lb
4"
2.6
3.0
3.1
2.1
1.7
1.7
1.7
1.7
1.6
2.1
6"
2.7
3.0
4.0
4.7
2.5
1.5
1.6
1.7
1.8
2.1
8j"
2.8
2.8*
4.0
3.7
5.2
4.0
1.9
2.2
2.2
2.2
11"
2.9
3.2
3.3
3.7
5.0
5.8
5.9
3.5
2.0
1.8
*Aspect Ratio = 1.33
** Underlined figures indicate autorotators
Sanitized Copy Approved for Release 2011/05/03: CIA-RDP78-03639A000500080001-1
 Sanitized Copy Approved for Release 2011/05/03: CIA-RDP78-03639A000500080001-1
TABLE G-4
VARIATION COEFFICIENTS (RT/To)
Aspect Ratio (Ratio of Length to Width)
Paper
Weight
Paper
Length
1.00
1.25
1.50
1.75
2.00
2.50
2.75
3.00
3.25
4.00
9 lb
4"
.31
.18
.30
.14
.13
.56
.45
.33
.24
.18
6"
.33
.56
.26
.51
.48
.34
.49
.67
.56
.30
8j"
.24
.22
.42
.37
.20
.16
.15
.34
.24
.80
11"
.37
.32
.25
.16
.18
.21
.12
.12
.19
.18
13 lb
4"
.12
.12
.13
.14
.27
.16
.34
.25
.34
.50
6"
.44
.23
.37
.55
.89
.87
.52
.59
.27
.09
81"
.31
.24
.31
.26
.25
.36
.27
.36
.60
.36
lift
.36
.22
.24
.40
.34
.26
.19
.33
.34
.56
16 lb
4"
.20
.11
.20
.32
.05
.23
.42
.23
.28
.63
6"
.32
.20
.63
.95
1.04
.28
.26
.36
.24
.17
8J"
.26
.30
.27
.69
.68
.69
.65
.91
.50
.30
11"
.31
.21
.29
.23
.20
.30
.25
.46
.18
.49
20 lb
4"
.19
.16
.16
.52
.05
.05
.07
.12
.65
.59
6"
.26
.13
.46
1.00
1.11
.23
.21
.22
.30
.22
4"
.35
.15
.58
.63
.71
1.01
.42
.23
.27
.40
11"
.24
.23
.42
.78
.58
.61
.62
.78
.57
.41
Sanitized Copy Approved for Release 2011/05/03: CIA-RDP78-03639A000500080001-1
 Sanitized Copy Approved for Release 2011/05/03: CIA-RDP78-03639A000500080001-1
TABLE OF GROUND PATTERN AREAS (ELLIPSES)
Major
Minor Axis (mi)
Axis
(mi)
4
6
8
10
12
14
16
18
20
5
16
24
31
39
47
55
63
71
79
10
31
47
63
79
94
110
126
141
157
15
47
71
94
118
141
165
188
212
236
20
63
94
126
157
188
220
251
283
314
25
79
118
157
196
236
275
314
353
393
30
94
141
188
236
283
330
377
424
471
35
110
165
220
275
330
385
440
495
550
40
126
188
251
314
377
440
503
565
628
45
141
212
283
353
424
495
565
636
707
50
157
236
314
393
471
549
628
707
785
55
173
259
346
432
518
605
691
778
864
60
188
283
377
471
565
660
754
848
943
65
204
306
408
511
613
715
817
919
1021
70
220
330
440
550
660
770
880
990
1100
75
236
353
471
589
707
825
943
1060
1178
80
251
377
503
628
754
880
1005
1131
1257
Sanitized Copy Approved for Release 2011/05/03: CIA-RDP78-03639A000500080001-1
 Sanitized Copy Approved for Release 2011/05/03: CIA-RDP78-03639A000500080001-1
LEAFLET DESCENT
Ground
Altitude Interval (thsds of ft)
Descent Rate
(ft/sec)
10
20
30
40
50
1.0
2.64
4.89
6.71
8.13
9.21
1.1
2.40
4.44
6.09
7.38
8.36
1.2
2.19
4.06
5.57
6.75
7.65
1.3
2.03
3.76
5.16
6.25
7.07
1.4
1.88
3.48
4.78
5.79
6.56
1.5
1.76
3.25
4.46
5.40
6.12
1.6
1.65
3.06
4.20
5.08
5.75
1.7
1.55
2.87
3.94
4.78
5.41
1.8
1.47
2.71
3.72
4.51
5.11
1.9
1.39
2.57
3.53
4.28
4.84
2.0
1.32
2.44
3.35
4.06
4.60
2.1
1.26
2.33
3.20
3.88
4.40
2.2
1.20
2.22
3.05
3.69
4.18
2.3
1.15
2.13
2.92
3.54
4.01
2.4
1.10
2.04
2.80
3.40
3.85
2.5
1.05
1.95
2.67
3.24
3.67
2.6
1.01
1.87
2.57
3.12
3.53
2.7
0.97
1.81
2.49
3.02
3.42
2.8
0.95
1.75
2.40
2.91
3.30
2.9
0.91
1.69
2.32
2.81
3.18
3.0
0.88
1.63
2.24
2.71
3.07
Sanitized Copy Approved for Release 2011/05/03: CIA-RDP78-03639A000500080001-1
 Sanitized Copy Approved for Release 2011/05/03: CIA-RDP78-03639A000500080001-1
LEAFLET DESCENT
TABLE A-1 (Cont'd)
TOTAL DESCENT TIMES (HOURS) - AUTOROTATORS
Ground
Altitude Interval (thsds of ft)
Descent Rate
(ft/sec)
10
20
30
40
50
3.1
0.85
1.58
2.17
2.62
2.97
3.2
0.83
1.53
2.10
2.55
2.89
3.3
0.80
1.48
2.03
2.46
2.79
3.4
0.78
1.44
1.97
2.39
2.71
3.5
0.75
1.40
1.91
2.32
2.63
Sanitized Copy Approved for Release 2011/05/03: CIA-RDP78-03639A000500080001-1
 Sanitized Copy Approved for Release 2011/05/03: CIA-RDP78-03639A000500080001-1
TIME FACTORS (HOURS) FOR THE DESCENT OF LEAFLETS
THROUGH 5, 000 FT INCREMENTS - AUTOROTATORS
Ground
Altitude Interval (thsds of ft)
Descent Rate
(ft/sec)
0-5
5-10
10-15
15-20
20-25
25-30
30-35
35-40
40-45
45-50
1.0
1.36
1.28
1.18
1.07
0.96
0.86
0.76
0.66
0.58
0.50
1.1
1.24
1.16
1.07
0.97
0.87
0.78
0.69
0.60
0.53
0.45
1.2
1.13
1.06
0.98
0.89
0.80
0.71
0.63
0.55
0.48
0.42
1.3
1.05
0.98
0.91
0.82
0.74
0.66
0.58
0.51
0.44
0.38
1.4
0.97
0.91
0.84
0.76
0.69
0.61
0.54
0.47
0.41
0.36
1.5
0.91
0.85
0.78
0.71
0.64
0.57
0.50
0.44
0.39
0.33
1.6
0.85
0.80
0.74
0.67
0.60
0.54
0.47
0.41
0.36
0.31
1.7
0.80
0.75
0.69
0.63
0.57
0.50
0.45
0.39
0.34
0.29
1.8
0.76
0.71
0.65
0.59
0.53
0.48
0.42
0.37
0.32
0.28
1.9
0.72
0.67
0.62
0.56
0.51
0.45
0.40
0.35
0.30
0.26
2.0
0.68
0.64
0.59
0.53
0.48
0.43
0.38
0.33
0.29
0.25
2.1
0.65
0.61
0.56
0.51
0.46
0.41
0.36
0.32
0.28
0.24
2.2
0.62
0.58
0.53
0.49
0.44
0.39
0.34
0.30
0.26
0.23
2.3
0.59
0.56
0.51
0.47
0.42
0.37
0.33
0.29
0.25
0.22
2.4
0.57
0.53
0.49
0.45
0.40
0.36
0.32
0.28
0.24
0.21
2.5
0.54
0.51
0.47
0.43
0.38
0.34
0.30
0.27
0.23
0.20
2.6
0.52
0.49
0.45
0.41
0.37
0.33
0.29
0.26
0.22
0.19
2.7
0.50
0.47
0.44
0.40
0.36
0.32
0.28
0.25
0.21
0.19
2.8
0.49
0.46
0.42
0.38
0.34
0.31
0.27
0.24
0.21
0.18
2.9
0.47
0.44
0.41
0.37
0.33
0.30
0.26
0.23
0.20
0.17
3.0
0.45
0.43
0.39
0.36
0.32
0.29
0.25
0.22
0.19
0.17
-15-
Sanitized Copy Approved for Release 2011/05/03: CIA-RDP78-03639A000500080001-1
 Sanitized Copy Approved for Release 2011/05/03: CIA-RDP78-03639A000500080001-1
TABLE A-2 (Cont'd)
TIME FACTORS (HOURS) FOR THE DESCENT OF LEAFLETS
THROUGH 5, 000 FT INCREMENTS - AUTOROTATORS
Ground
Altitude Interval (thsds of ft)
Descent Rates
(ft/sec) 0-5
5-10
10-15
15-20
20-25
25-30
30-35
35-40
40-45
45-50
3.1
0.44
0.41
0.38
0.35
0.31
0.28
0.24
0.21
0.19
0.16
3.2
0.43
0.40
0.37
0.33
0.30
0.27
0.24
0.21
0.18
0.16
3.3
0.41
0.39
0.36
0.32
0.29
0.26
0.23
0.20
0.18
0.15
3.4
0.40
0.38
0.35
0.31
0.28
0.25
0.22
0.20
0.17
0.15
3.5
0.39
0.36
0.34
0.31
0.27
0.24
0.22
0.19
0.17
0.14
Sanitized Copy Approved for Release 2011/05/03: CIA-RDP78-03639A000500080001-1
 Sanitized Copy Approved for Release 2011/05/03: CIA-RDP78-03639A000500080001-1
TIME FACTORS (HOURS) FOR THE DESCENT OF LEAFLETS
TO BE USED WITH STANDARD WIND DATA - AUTOROTATING
Ground
Altitude (thsds of ft)
Descent Rate
(ft/sec)
0
1
2
3
4
5
6
7
8
9
10
12
1.0
.14
.28
.27
.27
.27
.27
.26
.26
.25
.25
.37
.48
1.1
.13
.25
.25
.25
.24
.24
.24
.23
.23
.23
.33
.43
1.2
.12
.23
.23
.23
.22
.22
.22
.21
.21
.21
.30
.40
1.3
.11
.21
.21
.21
.21
.20
.20
.20
.20
.19
.28
.37
1.4
.10
.20
.20
.19
.19
.19
.19
.18
.18
.18
.26
.34
1.5
.09
.18
.18
.18
.18
.18
.17
.17
.17
.17
.24
.32
1.6
.09
.17
.17
.17
.17
.17
.16
.16
.16
.16
.23
.30
1.7
.08
.16
.16
.16
.16
.16
.15
.15
.15
.15
.21
.28
1.8
.08
.15
.15
.15
.15
.15
.15
.14
.14
.14
.20
.26
Ground
Altitude (thsds of ft)
Descent Rate
(ft/sec)
14
16
18
20
23
25
30
35
40
45
50
1.0
.46
.44
.42
.51
.48
.63
.81
.71
.62
.54
.24
1.1
.42
.40
.39
.46
.43
.57
.73
.64
.56
.49
.22
1.2
.38
.37
.35
.42
.40
.52
.67
.59
.52
.45
.20
1.3
?35
.34
.33
.39
?37
.48
.62
.55
.48
.41
.18
1.4
.33
.32
.30
.36
.34
.45
.58
.51
.44
.38
.17
1.5
.31
.29
.28
.34
.32
.42
.54
.47
.41
.36
.16
1.6
.29
.28
.27
.32
.30
.40
.50
.44
.39
.34
.15
1.7
.27
.26
.25
.30
.28
.37
.47
.42
.36
.32
.14
1.8
.25
.25
.24
.28
.27
.35
.45
.39
.34
.30
.13
-17-
Sanitized Copy Approved for Release 2011/05/03: CIA-RDP78-03639A000500080001-1
 Sanitized Copy Approved for Release 2011/05/03: CIA-RDP78-03639A000500080001-1
TABLE A-3 (Cont'd)
TIME FACTORS (HOURS) FOR THE DESCENT OF LEAFLETS
TO BE USED WITH STANDARD WIND DATA - AUTOROTATING
Ground
Altitude (thsds of ft)
Descent Rate
(ft/sec) 0
1
2
3
4 5
6
7
8
9
10
12
1.9 .07
.15
.14
.14
.14 .14
.14
.14
.13
.13
.19
.25
2.0 .07
.14
.14
.14
.13 .13
.13
.13
.13
.13
.18
.24
2.1 .07
.13
.13
.13
.13 .13
.12
.12
.12
.12
.17
.23
2.2 .06
.13
.12
.12
.12 .12
.12
.12
.12
.11
.17
.22
2.3 .06
.12
.12
.12
.12 .12
.11
.11
.11
.11
.16
.21
2.4 .06
.12
.11
.11
.11 .11
.11
.11
.11
.10
.15
.20
2.5 06
.11
.11
.11
.11 .11
.10
.10
.10
.10
.15
.19
2.6 .05
.11
.11
.10
.10 .10
.10
.10
.10
.10
.14
.18
2.7 .05
.10
.10
.10
.10 .10
.10
.10
09
09
.14
.18
Ground
Altitude (thsds of ft)
Descent Rate
(ft/sec) 14
16
18
20
23 25
30
35
40
45
50
1.9 .24
.23
.22
.27
.25 .33
.42
.37
.33
.28
.13
2.0 .23
.22
.21
.25
.24 .31
.40
.35
.31
.27
.12
2.1 .22
.21
.20
.24
.23 .30
.38
.34
.30
.26
.11
2.2 .21
.20
.19
.23
.22 .28
.37
.32
.28
.24
.11
2.3 .20
.19
.18
.22
.21 .27
.35
.31
.27
.23
.10
2.4 .19
.18
.18
.21
.20 .26
.34
.30
.26
.22
.10
2.5 .18
.18
.17
.20
.19 .25
.32
.28
.25
.22
.10
2.6 .18
.17
.16
.19
.18 .24
.31
.27
.24
.21
.09
2.7 .17
.16
.16
.19
.18 .23
.30
.26
.23
.20
.09
-18-
Sanitized Copy Approved for Release 2011/05/03: CIA-RDP78-03639A000500080001-1
 Sanitized Copy Approved for Release 2011/05/03: CIA-RDP78-03639A000500080001-1
TIME FACTORS (HOURS) FOR THE DESCENT OF LEAFLETS
TO BE USED WITH STANDARD WIND DATA - AUTOROTATING
Ground
Altitude (thsds of ft)
Descent Rate
(ft/sec)
0
1
2
3
4
5
6
7
8
9
10
12
2.7
.05
.10
.10
.10
.10
.10
.10
.10
.09
.09
.14
.18
2.8
.05
.10
.10
.10
.10
.09
.09
.09
.09
.09
.13
.17
2.9
.05
.10
.09
.09
.09
.09
.09
.09
.09
.09
.13
.16
3.0
.05
.09
.09
.09
.09
.09
.09
.09
.08
.08
.12
.16
3.1
.04
.09
.09
.09
.09
.09
.08
.08
.08
.08
.12
.15
3.2
.04
.09
.09
.08
.08
.08
.08
.08
.08
.08
.11
.15
3.3
.04
.08
.08
.o8
.08
.08
.o8
.08
.08
08
.11
.14
3.4
.04
.08
.08
.08
.08
.08
.08
.08
.07
.07
.11
.14
3.5
.04
.08
.08
.o8
.08
.o8
.07
.07
.07
.07
.10
.14
Ground
Descent Rate
(ft/sec)
14
16
18
20
23
25
30
35
40
45
50
2.7
.17
.16
.16
.19
.18
.23
.30
.26
.23
.20
.09
2.8
.16
.16
.15
.18
.17
.22
.29
.25
.22
.19
.09
2.9
.16
.15
.15
.17
.16
.22
.28
.24
.21
.19
08
3.0
.15
.15
.14
.17
.16
.21.
.27
.24
.21
.18
.08
3.1
.15
.14
.14
.16
.15
.2.0
.26
.23
.20
.17
.08
3.2
.14
.14
.13
.16
.15
.20
.25
.22
.19
.17
.08
3.3
.14
.13
.13
.15
.14
.19
.24
.21
.19
.16
.07
3.4
.13
.13
.12
.15
.14
.18
.24
.21
.18
.16
.07
3.5
.13
.13
.12
.14
.14
.18
.23
.20
.18
.15
.07
-19-
Sanitized Copy Approved for Release 2011/05/03: CIA-RDP78-03639A000500080001-1
 Sanitized Copy Approved for Release 2011/05/03: CIA-RDP78-03639A000500080001-1
DESCENT RATES AT DIFFERENT ALTITUDES
FOR AUTOROTATING TYPE LEAFLETS
(ft/sec)
Ground
Altitude (thsds of ft)
Descent Rate
(ft/sec)
5
10
15
20
25
30
35
40
45
50
1.0
1.0
1.1
1.2
1.4
1.5
1.7
2.0
2.2
2.6
3.0
1.1
1.2
1.2
1.4
1.5
1.7
1.9
2.2
2.5
2.8
3.3
1.2
1.3
1.4
1.5
1.6
1.8
2.1
2.4
2.7
3.1
3.6
1.3
1.4
1.5
1.6
1.8
2.0
2.2
2.5
2.9
3.4
3.9
1.4
1.5
1.6
1.7
1.9
2.1
2.4
2.7
3.1
3.6
4.2
1.5
1.6
1.7
1.9
2.1
2.3
2.6
2.9
3.4
3.9
4.5
1.6
1.7
1.8
2.0
2.2
2.4
2.8
3.1
3.6
4.1
4.8
1.7
1.8
1.9
2.1
2.3
2.6
2.9
3.3
3.8
4.4
5.1
1.8
1.9
2.0
2.2
2.5
2.8
3.1
3.5
4.0
4.7
5.4
1.9
2.0
2.1
2.3
2.6
2.9
3.3
3.7
4.3
4.9
5.7
2.0
2.1
2.3
2.5
2.7
3.1
3.4
3.9
4.5
5.2
6.o
2.1
2.2
2.4
2.6
2.9
3.2
3.6
4.1
4.7
5.4
6.3
2.2
2.3
2.5
2.7
3.0
3.4
3.8
4.3
4.9
5.7
6.6
2.3
2.4
2.6
2.8
3.1
3.5
4.0
4.5
5.2
5.9
6.9
2.4
2.5
2.7
3.0
3.3
3.7
4.1
4.7
5.4
6.2
7.2
2.5
2.6
2.8
3.1
3.4
3.8
4.3
4.9
5.6
6.5
7.5
2.6
2.7
2.9
3.2
3.6
4.0
4.5
5.1
5.8
6.7
7.8
2.7
2.8
3.1
3.3
3.7
4.1
4.7
5.3
6.1
7.0
8.1
2.8
2.9
3.2
3.5
3.8
4.3
4.8
5.5
6.3
7.2
8.4
2.9
3.0
3.3
3.6
4.0
4.4
5.0
5.7
6.5
7.5
8.7
-20-
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 Sanitized Copy Approved for Release 2011/05/03: CIA-RDP78-03639A000500080001-1
DESCENT RATES AT DIFFERENT ALTITUDES
FOR AUTOROTATING TYPE LEAFLETS
(ft/sec)
Ground
Altitude (theds of ft)
Descent Rate
(ft/sec)
5
10
15
20
25
30
35
40
45
50
3.0
3.1
3.4
3.7
4.1
4.6
5.2
5.9
6.7
7.8
9.0
3.1
3.3
3.5
3.8
4.2
4.7
5.3
6.1
6.9
8.0
9.3
3.2
3.4
3.6
4.0
4.4
4.9
5.5
6.3
7.2
8.3
9.6
3.3
3.5
3.7
4.1
4.5
5.0
5.7
6.5
7.4
8.5
9.9
3.4
3.6
3.8
4.2
4.6
5.2
5.9
6.7
7.6
8.8
10.2
3.5
3.7
4.0
4.3
4.8
5.3
6.0
6.9
7.8
9.0
10.5
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 Sanitized Copy Approved for Release 2011/05/03: CIA-RDP78-03639A000500080001-1
TOTAL DESCENT TIMES (HOURS) - NON-AUTOROTATORS
Ground
Altitude (thsds of ft)
Descent Rate
(ft/sec)
10
20
30
40
50
2.0
1.35
2.52
3.43
4.07
4.48
2.1
1.27
2.38
3.25
3.86
4.25
2.2
1.22
2.28
3.11
3.69
4.06
2.3
1.17
2.18
2.98
3.54
3.89
2.4
1.12
2.09
2.85
3.38
3.72
2.5
1.07
2.00
2.73
3.24
3.56
2.6
1.03
1.93
2.63
3.12
3.44
2.7
1.00
1.86
2.53
3.00
3.30
2.8
0.96
1.80
2.45
2.91
3.20
2.9
0.92
1.72
2.35
2.79
3.07
3.0
0.90
1.68
2.29
2.72
2.99
3.1
0.86
1.61
2.20
2.62
2.88
3.2
0.84
1.57
2.14
2.54
2.79
3.3
0.82
1.53
2.09
2.47
2.72
3.4
0.79
1.48
2.02
2.40
2.63
3.5
0.76
1.43
1.95
2.31
2.54
3.6
0.74
1.39
1.89
2.25
2.48
3.7
0.72
1.35
1.85
2.20
2.42
3.8
0.71
1.32
1.80
2.14
2.35
3.9
0.69
1.28
1.75
2.08
2.29
4.0
0.67
1.26
1.72
2.04
2.24
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 Sanitized Copy Approved for Release 2011/05/03: CIA-RDP78-03639A000500080001-1
Ground
Altitude (thsds of ft)
Descent Rate
(ft/sec)
10
20
30
40
50
4.1
0.65
1.22
1.67
1.98
2.18
4.2
0.64
1.19
1.62
1.93
2.12
4.3
0.63
1.17
1.60
1.89
2.08
4.4
0.61
1.14
1.55
1.84
2.02
4.5
0.59
1.11
1.52
1.81
1.99
4.6
0.59
1.10
1.49
1.77
1.95
4.7
0.57
1.07
1.46
1.73
1.91
4.8
0.56
1.04
1.42
1.69
1.86
4.9
0.55
1.03
i.4o
1.66
1.82
5.0
0.53
0.99
1.36
1.62
1.78
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 Sanitized Copy Approved for Release 2011/05/03: CIA-RDP78-03639A000500080001-1
LEAFLET DESCENT
TIME FACTORS (HOURS) FOR THE DESCENT OF LEAFLETS
THROUGH 5, 000-FT INCREMENTS - NON-AUTOROTATORS
Ground
Altitude Interval (thsds of ft)
Descent Rate
(ft/sec)
0-5
5-10
10-15
15-20
20-25
25-30
30-35
35-40
40-45
4
0
5-5
1.0
1.37
1.31
1.22
1.11
0.98
0.84
0.71
0.58
0.46
0.35
2.0
0.69
0.66
0.61
0.56
0.49
0.42
0.35
0.29
0.23
0.18
2.1
o.65
0.62
0.58
0.53
0.47
0.40
0.34
0.27
0.22
0.17
2.2
0.62
0.60
0.56
0.50
0.45
0.38
0.32
0.26
0.21
0.16
2.3
0.60
0.57
0.53
0.48
0.43
0.37
0.31
0.25
0.20
0.15
2.4
0.57
0.55
0.51
0.46
0.41
0.35
0.29
0.24
0.19
0.15
2.5
0.55
0.52
0.49
0.44
0.39
0.34
0.28
0.23
0.18
0.14
2.6
0.53
0.50
0.47
0.43
0.38
0.32
0.27
0.22
0.18
0.14
2.7
0.51
0.49
0.45
0.41
0.36
0.31
0.26
0.21
0.17
0.13
2.8
0.49
0.47
0.44
0.40
0.35
0.30
0.25
0.21
0.16
0.13
2.9
0.47
0.45
0.42
0.38
0.34
0.29
0.24
0.20
0.16
0.12
3.0
0.46
0.44
0.41
0.37
0.33
0.28
0.24
0.19
0.15
0.12
3.1
0.44
0.42
0.39
0.36
0.32
0.27
0.23
0.19
0.15
0.11
3.2
0.43
0.41
0.38
0.35
0.31
0.26
0.22
0.18
0.14
0.11
3.3
0.42
0.40
0.37
0.34
0.30
0.26
0.25
0.17
0.14
0.11
3.4
0.40
0.39
0.36
0.33
0.29
0.25
0.21
0.17
0.13
0.10
3.5
0.39
0.37
0.35
0.32
0.28
0.24
0.20
0.16
0.13
0.10
3.6
0.38
0.36
0.34
0.31
0.27
0.23
0.20
0.16
0.13
0.10
3.7
0.37
0.35
0.33
0.30
0.27
0.23
0.19
0.16
0.12
0.10
3.8
0.36
0.35
0.32
0.29
0.26
0.22
0.19
0.15
0.12
0.09
3.9
0.35
0.34
0.31
0.28
0.25
0.22
0.18
0.15
0.12
0.09
Sanitized Copy Approved for Release 2011/05/03: CIA-RDP78-03639A000500080001-1
 Sanitized Copy Approved for Release 2011/05/03: CIA-RDP78-03639A000500080001-1
TIME FACTORS (HOURS) FOR THE DESCENT OF LEAFLETS
THROUGH 5, 000-FT INCREMENTS - NON-AUTOROTATORS
Ground
Altitude Interval (thsds of ft)
Descent Rate
(ft/sec)
0-5
5-10
10-15
15-20
20-25
25-30
30-35
35-40
40-45
45-50
4.0
0.34
0.33
0.31
0.28
0.25
0.21
0.18
0.14
0.11
0.09
4.1
0.33
0.32
0.30
0.27
0.24
0.21
0.17
0.14
0.11
0.09
4.2
0.33
0.31
0.29
0.26
0.23
0.20
0.17
0.14
0.11
0.08
4.3
0.32
0.31
0.28
0.26
0.23
0.20
0.16
0.13
0.11
0.08
4.4
0.31
0.30
0.28
0.25
0.22
0.19
0.16
0.13
0.10
0.08
4.5
0.30
0.29
0.27
0.25
0.22
0.19
0.16
0.13
0.10
0.08
4.6
0.30
0.29
0.27
0.24
0.21
0.18
0.15
0.13
0.10
0.08
4.7
0.29
0.28
0.26
0.24
0.21
0.18
0.15
0.12
0.10
0.08
4.8
0.29
0.27
0.25
0.23
0.20
0.18
0.15
0.12
0.10
0.07
4.9
0.28
0.27
0.25
0.23
0.20
0.17
0.14
0.12
0.09
0.07
5.0
0.27
0.26
0.24
0.22
0.20
0.17
0.14
0.12
0.09
0.07
-25-
Sanitized Copy Approved for Release 2011/05/03: CIA-RDP78-03639A000500080001-1
 Sanitized Copy Approved for Release 2011/05/03: CIA-RDP78-03639A000500080001-1
LEAFLET DESCENT
TIME FACTORS (HOURS) FOR THE DESCENT OF LEAFLETS
TO BE USED WITH STANDARD WIND DATA - NON-AUTOROTATING
Ground
Altitude (thsds of ft)
Descent Rate
(ft/sec)
0
1
2
3
4
5
6
7
8
9
10
12
1.0
.10
.28
.28
.27
.27
.27
.27
.26
.26
.26
.38
.49
2.0
.05
.14
.14
.14
.14
.13
.13
.13
.13
.13
.19
.25
2.1
.05
.13
.13
.13
.13
.13
.13
.13
.12
.12
.18
.24
2.2
.04
.13
.12
.12
.12
.12
.12
.12
.12
.12
.17
.22
2.3
.04
.12
.12
.12
.12
.12
.12
.11
.11
.11
.17
.21
2.4
.04
.12
.11
.11
.11
.11
.11
.11
.11
.11
.16
.21
2.5
.04
.11
.11
.11
.11
.11
.11
.11
.10
.10
.15
.20
2.6
.04
.11
.11
.11
.10
.10
.10
.10
.10
.10
.15
.19
2.7
.04
.1.0
.10
.10
.10
.10
.10
.10
.10
.10
.14
.18
Ground
Altitude (thsds of ft)
Descent Rate
(ft/sec)
14
16
18
20
23
25
30
35
40
45
50
1.0
.48
.46
.44
.52
.49
.63
.78
.64
.52
.42
.16
2.0
.24
.23
.22
.26
.24
.31
.39
.32
.26
.21
.08
2.1
.23
.22
.21
.25
.23
.30
.37
.31
.25
.20
.08
2.2
.22
.21
.20
.24
.22
.28
.35
.29
.23
.19
.07
2.3
.21
.20
.19
.23
.21
.27
.34
.28
.22
.18
.07
2.44
.20
.19
.18
.22
.20
.26
.32
.27
.22
.18
.07
2.5
.19
.18
.18
.21
.19
.25
.31
.26
.21
.17
.07
2.6
.18
.18
.17
.20
.19
.24
.30
.25
.20
.16
.06
2.7
.18
.17
.16
.19
.18
.23
.29
.24
19
.16
.06
-z6-
Sanitized Copy Approved for Release 2011/05/03: CIA-RDP78-03639A000500080001-1
 Sanitized Copy Approved for Release 2011/05/03: CIA-RDP78-03639A000500080001-1
TIME FACTORS (HOURS) FOR THE DESCENT OF LEAFLETS
TO BE USED WITH STANDARD WIND DATA - NON-AUTOROTATING
Ground
Altitude (thsds of ft)
Descent Rate
(ft/sec)
0
1
2
3
4
5
6
7
8
9
10
12
2.8
.03
.10
.10
.10
.10
.10
.10
.09
.09
.09
.14
.18
2.9
.03
.10
.09
.09
.09
.09
.09
.09
.09
.09
.13
.17
3.0
.03
.09
.09
.09
.09
.09
.09
.09
.09
.09
.13
.16
3.1
.03
.09
.09
.09
.09
.09
.09
.09
.08
.08
.12
.16
3.2
.03
.09
.09
.09
.09
.08
.08
.08
.08
.08
.12
.15
3.3
.03
.08
.08
.08
.08
.08
.08
.08
.08
.08
.12
.15
3.4
.03
.08
.08
.08
.08
.08
.08
.08
.08
.08
.11
.15
3.5
.03
.08
.08
.08
.08
.08
.08
.08
.07
.07
.11
.14
3.6
.03
.08
.08
.08
.08
.07
.07
.07
.07
.07
.11
.14
Ground
Altitude (thsds of ft)
Descent Rate
(ft/sec)
14
16
18
20
23
25
30
35
40
45
50
2.8
.17
.16
.16
.19
.17
.22
.28
.23
.18
.15
.06
2.9
.16
.16
.15
.18
.17
.22
.27
.22
.18
.15
.06
3.0
.16
.15
.15
.17
.16
.21
.26
.21
.17
.14
.05
3.1
.15
.15
.14
.17
.16
.20
.25
.21
.17
.14
.05
3.2
.15
.14
.14
.16
.15
.20
.24
.20
.16
.13
.05
3.3
.14.
.14
.13
.16
.15
.19
.24
.19
.16
.13
.05
3.4
.14
.13
.13
.15
.14
.18
.23
.19
.15
.12
.05
3.5
.14
.13
.13
.15
.14
.18
.22
.18
.15
.12
.05
3.6
.13
.13
.12
.14
.14
.17
.22
.18
.14
.12
.05
-27-
Sanitized Copy Approved for Release 2011/05/03: CIA-RDP78-03639A000500080001-1
 Sanitized Copy Approved for Release 2011/05/03: CIA-RDP78-03639A000500080001-1
TABLE NA-3 (Cont'd)
TIME FACTORS (HOURS) FOR THE DESCENT OF LEAFLETS
TO BE USED WITH STANDARD WIND DATA - NON-AUTOROTATING
Ground
Altitude (thsds of ft)
Descent Rate
(ft/sec)
0
1
2
3
4 5 6 7
8
9
10
12
3.7
.03
.07
.07
.07
.07 .07 .07 .07
.07
.07
.10
.13
3.8
.03
.07
.07
.07
.07 .07 .07 .07
.07
.07
.10
.13
3.9
.02
.07
.07
.07
.07 .07 .07 .07
.07
.07
.10
.13
4.0
.02
.07
.07
.07
.07 .07 .07 .07
.07
06
.10
.12
4.1
.02
.07
.07
.07
.07 .07 .07 06
06
06
.09
.12
4.2
.02
.07
.07
.07
06 o6 .06 06
06
06
.09
.12
4.3
.02
.o6
.06
.06
.06 .06 .06 .06
.06
.06
.09
.11
4.4
.02
.06
.06
.06
.06 .06 .06 .06
06
06
09
.11
4.5
.02
.06
.06
.06
.06 .06 .06 06
06
06
08
.11
Ground
Altitude (thsds of ft)
Descent Rate
(ft/sec)
14
16
18
20
23 25 30 35
40
45
50
3.7
.13
.13
.12
.14
.13? .17 .21 .17
.14
.11
o4
3.8
.13
.12
.12
.14
.13 .16 .20 .17
.14
.11
04
3.9
.12
.12
.11
.13
.12 .16 .20 .16
.13
.11
.04
4.0
.12
.11
.11
.13
.12 .16 .19 .16
.13
.11
o4
4.1
.12
.11
.11
.13
.12 .15 .19 .16
.13
.10
.04
4.2
.11
.11
.10
.12
.12 .15 .18 .15
.12
.10
.04
4
.3
.11
.11
.10
.12
.11 .15 .18 .15
.12
.10
.04
4
.4
.11.
.10
.10
.12
.11 .14 .18 .15
.12
.10
.04
4
.5
.11
.1.0
.10
.12
.11 .14 .17 .14
.11
.09
.04
-28-
Sanitized Copy Approved for Release 2011/05/03: CIA-RDP78-03639A000500080001-1
 Sanitized Copy Approved for Release 2011/05/03: CIA-RDP78-03639A000500080001-1
LEAFLET DESCENT
TIME FACTORS (HOURS) FOR THE DESCENT OF LEAFLETS
TO BE USED WITH STANDARD WIND DATA - NON-AUTOROTATING
Ground
Altitude (thsds of ft)
Descent Rate
(ft/
c)
0
1
2
3
4
5
6
7
8
9
10
12
se
4.6
.02
.06
.06
.06
.06
o6
.06
.06
.06
o6
.08
.11
4.7
.02
.06
.06
.06
.06
.06
.06
.06
.c6
.05
.08
.11
4.8
.02
.06
.06
.06
.06
.06
.06
.05
.05
.05
.08
.10
4.9
.02
.06
.06
.06
.06
.05
.05
.05
.05
.05
.08
.10
5.0
.02
.06
.06
.05
.05
.05
.05
.05
.05
.05
.08
.10
Ground
Altitude (thsds of ft)
Descent Rate
(ft/sec)
14
16
18
20
23
25
30
35
40
45
50
4.6
.10
.10
.10
.11
.11
.14
.17
.14
.11
.09
.04
4.7
.10
.10
.09
.11
.10
.13
.17
.14
.11
.09
.03
4.8
.10
.10
.09
.11
.10
.13
.16
.13
.11
.09
.03
4.9
.10
.09
.09
.11
.10
.13
.16
.13
.11
.09
.03
5.0
.10
.09
.09
.10
.10
.13
.16
.13
.10
.08
.03
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DESCENT RATES AT DIFFERENT ALTITUDES
FOR NON-AUTOROTATING TYPE LEAFLETS
(ft/sec)
Ground
Altitude (thsds of ft)
Descent Rate
(ft/sec)
5
10
15
20
25
30
35
40
45
50
2.0
2.1
2.2
2.4
2.7
3.0
3.6
4.3
5.4
6.9
9.0
2.1
2.2
2.3
2.5
2.8
3.2
3.8
4.6
5.7
7.2
9.5
2.2
2.3
2.4
2.6
2.9
3.3
3.9
4.8
5.9
7.6
9.9
2.3
2.4
2.5
2.7
3.0
3.5
4.1
5.0
6.2
7.9
10.4
2.4
2.5
2.6
2.8
3.2
3.6
4.3
5.2
6.5
8.3
10.9
2.5
2.6
2.7
3.0
3.3
3.8
4.5
5.4
6.7
8.6
11.3
2.6
2.7
2.8
3.1
3.4
4.0
4.7
5.6
7.0
9.0
11.8
2.7
2.8
2.9
3.2
3.6
4.1
4.8
5.9
7.3
9.3
12.2
2.8
2.9
3.1
3.3
3.7
4.3
5.0
6.1
7.6
9.6
12.7
2.9
3.0
3.2
3.4
3.8
4.4
5.2
6.3
7.8
10.0
13.1
3.0
3.1
3.3
3.6
4.0
4.6
5.4
6.5
8.1
10.3
13.6
3.1
3.2
3.4
3.7
4.1
4.7
5.6
6.7
8.4
10.7
14.0
3.2
3.3
3.5
3.8
4.2
4.9
5.7
6.9
8.6
11.0
14.5
3.3
3.4
3.6
3.9
4.4
5.0
5.9
7.2
8.9
11.4
14.9
3.4
3.5
3.7
4.0
4.5
5.2
6.1
7.4
9.2
11.7
15.4
3.5
3.6
3.8
4.2
4.6
5.3
6.3
7.6
9.4
12.1
15.8
3.6
3.7
3.9
4.3
4.8
5.5
6.4
7.8
9.7
12.4
16.3
3.7
3.8
4.0
4.4
4.9
5.6
6.6
8.0
10.0
12.7
16.7
3.8
3.9
4.1
4.5
5.0
5.8
6.8
8.2
10.2
13.1
17.2
3.9
4.0
4.3
4.6
5.2
5.9
7.0
8.5
10.5
13.4
17.6
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TABLE NA-4 (Cont'd)
DESCENT RATES AT DIFFERENT ALTITUDES
FOR NON-AUTOROTATING TYPE LEAFLETS
(ft/ sec)
Ground
Altitude (thsds of ft)
Descent Rate
(ft/sec)
5
10
15
20
25
30
35
40
45
50
4.0
4.1
4.4
4.7
5.3
6.1
7.2
8.7
10.8
13.8
18.1
4.1
4.2
4.5
4.9
5.4
6.2
7.3
8.9
11.1
14.1
18.5
4.2
4.3
4.6
5.0
5.6
6.4
7.5
9.1
11.3
14.5
19.0
4.3
4.4
4.7
5.1
5.7
6.5
7.7
9.3
11.6
14.8
19.4
4.4
4.5
4.8
5.2
5.8
6.7
7.9
9.5
11.9
15.2
19.9
4.5
4.6
4.9
5.3
6.0
6.8
8.1
9.8
12.1
15.5
20.3
4.6
4.7
5.0
5.5
6.1
7.0
8.2
10.0
12.4
15.8
20.8
4.7
4.8
5.1
5.6
6.2
7.1
8.4
10.2
12.7
16.2
21.3
4.8
4.9
5.2
5.7
6.4
7.3
8.6
10.4
12.9
16.5
21.7
4.9
5.1
5.3
5.8
6.5
7.4
8.8
10.6
13.2
16.9
22.2
5.0
5.2
5.5
5.9
6.6
7.6
9.0
10.8
13.5
17.2
22.6
5.1
5.3
5.6
6.1
6.8
7.8
9.1
11.1
13.8
17.6
23.1
5.2
5.4
5.7
6.2
6.9
7.9
9.3
11.3
14.0
17.9
23.5
5.3
5.5
5.8
6.3
7.0
8.1
9.5
11.5
14.3
18.3
24.0
5.4
5.6
5.9
6.4
7.2
8.2
9.7
11.7
14.6
18.6
24.4
5.5
5.7
6.o
6.5
7.3
8.4
9.9
11.9
14.8
18.9
24.9
5.6
5.8
6.1
6.6
7.4
8.5
10.0
12.1
15.1
19.3
25.3
5.7
5.9
6.2
6.8
7.6
8.7
10.2
12.4
15.4
19.6
25.8
5.8
6.0
6.3
6.9
7.7
8.8
10.4
12.6
15.6
20.0
26.2
5.9
6.1
6.4
7.0
7.8
9.0
10.6
12.8
15.9
20.3
26.7
6.o
6.2
6.5
7.1
8.0
9.1
10.7
13.0
16.2
20.7
27.1
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LEAFLET DESCENT
MAKING THE COMPUTATIONS
Computation Sheet - The suggested computation sheet and illustrative
examples of the use of the tables follow. The sheet is divided into
three major sections. In the upper left are entered the wind speeds
and azimuth angles of the predicted winds for the 5000-foot altitude
increments of interest, I To this are added the time factors in hours
for the leaflet type selected, with a column provided for the product of
the appropriate time factor and the wind speed in each 5000-foot incre-
ment. In the upper right are listed the launch date, time, and site; the
target; and the release altitude. Immediately below this are the data
on the leaflet type selected. The bottom half of the sheet is for record-
ing the computations of drift and determining the ground pattern area
and leaflet density. A sheet of graph paper lined to a convenient scale
(such as 10 squares to the inch) should be obtained also for plotting the
vector results of the horizontal drift distance.
Example No. 1 - Example No. 1 is for 4 x 6 inch leaflets printed on
16-lb. paper released at a height of 37, 000 feet, and with wind speeds
and azimuth angles as indicated on the form. The first thing to do is to
refer to Table G-1, where it is seen that this leaflet size corresponds
to an aspect ratio of 1. 5. The number of leaflets per pound as found in
Table G-2 is 487. Referring to Table G-3, it is seen that a 16-lb. leaf-
let with a length of 6" and an aspect ratio of 1, 5 has a ground rate of
descent (Vo) of 3, 3 ft/sec and falls with a non-autorotating motion. The
coefficient of variation (RT/To) as found in Table G-4 is 0. 63.
The time factors for a non-autorotating leaflet with a Vo= 3. 3
ft/sec may be found in Table NA-2, These values are listed in the ap-
propriate column in the upper left of the computation sheet, and the
factors multiplied by the wind speed corresponding to that altitude in-
crement give the horizontal drift distance through each 5000-foot inter-
val. These drift distances are next plotted on graph paper to obtain
the overall drift. The tail of the first vector represents the release
1 The azimuthal angles are the direction from which the winds are
blowing on a 360 degree scale moving in a clockwise direction from due
north. For example, a 900 wind is blowing from east to west, a 1800
wind from south to north, a 2700 wind from west to east, and a 3600
wind from north to south.
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LEAFLET DESCENT
Height Time
Wind Horiz. Drift Azimuth
Date
Increments Factor
(thsds of ft) hours)
Speed Distance Angle
(knots) (naut. mi.) (deg)
Time of Launch
50-45
Launch Site
45-40
40-35
35-30
30-25
Paper Weight
25-20
Size
20-15
Aspect Ratio
15-10
RT
10-5
To
Vo
Autor otator
Non-autorotator
Leaflets/lb
Computations
Total horizontal drift vector from release to impact:
Maximum deviation normal to net vector: _
Ground Dispersion Pattern:
Major Axis
Minor Axis
Area
Payload
Number of leaflets
Mean density
Leaflets/mil - 2800 = leaflets/10, 000 ft2
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point. The vector is drawn along a line parallel to the azimuth angle of
the wind, the length of the vector corresponding to the horizontal drift
distance. The second vector has its tail at the head of the first vector
and so forth until the last vector is plotted. In this case the release
altitude was 37, 000 feet, and therefore the first vector is only 2/5 of
that shown on the form sheet, i, e., 4. 0 miles rather than 10, 2, The
subsequent vectors are, of course, all full length with the possible ex-
ception of the last one, which will have to be shortened if the impact
area is above sea level. In this example it is assumed that the eleva-
tion of the target is essentially the same as sea level, so no correction
need be made.
Having plotted the vectors for each successive altitude incre-
ment, the resultant horizontal drift vector is now drawn from the re-
lease point (the tail of the first vector) to the impact point (the head of
the last vector). Measuring the length and azimuth of the resultant
vector yields the overall drift distance and direction, in this case 57
nautical miles and 2820, respectively, Finding the maximum deviation
normal to the resultant is done simply by inspection. It turns out to be
8 nautical miles for this example.
It should be noted that, since the winds are reported in knots
rather than in miles per hour, the distances plotted are nautical miles
and must be multiplied by the factor 1, 15 to convert them to statute
miles. In other words, the resultant drift vector is 66 statute miles
(1. 15 times 57 nautical miles) and the maximum deviation normal to it
is 9 statute miles (1. 15 times 8 nautical miles).
Having obtained the total horizontal drift and the maximum devi-
ation normal to it, these values are recorded in the section for compu-
tations. The size of the ground dispersion pattern can now be deter-
mined. The major axis of the ellipse is the total drift multiplied by the
variation coefficient, while the minor axis is the sum of one-half of the
release height (in miles)1 plus the maximum normal deviation times the
variation coefficient. The major axis here is 66 times 0. 63, or 41
miles; the minor axis is 13 miles, The major and minor axes thus de-
termined, the area is found from the formulaA= 4abto be 420 square
miles.
1 This is the ratio of the release height in feet to 5280 feet, the result
being the release height in miles.
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Dispersion Density - Knowing the size of the payload and the number of
leaflets per pound permits calculation of the total number of leaflets
released, and this value divided by the above calculated area figure
yields the average density in leaflets per square mile. The payload
here was 400 pounds and the number of leaflets per pound was 487 giv-
ing a total of 195, 000 leaflets released. The average density then is
195, 000 = 420, or 464 leaflets/mi2.
A more meaningful figure, however, is the average number of
leaflets in each square that is 100 feet on a side (i. e. , in 10, 000 square
feet). This can be obtained by dividing the number of leaflets per
square mile by 2800; thus 464 divided by 2800 yields a density of 0, 16
leaflets per 10, 000 square feet. In other words, there is only one leaf-
let per 60, 000 square feet on the average. A reasonable density is
between 1 and 10 leaflets per 10, 000 square feet.
It is useful to draw the ground pattern on graph paper. The -
center of the ellipse is placed at the predicted point of impact and the
major and minor axes measured out with the major axis being along the
resultant drift vector and the minor axis normal to it. The ellipse can
then be drawn and shaded in to show the general size of the ground pat-
tern more distinctly.
Example No. 2 - The leaflet in Example No. 2 was selected because it
has a slower ground level rate of descent (Vo) and a considerably
smaller variation coefficient, while still being of the non-autorotating
leaflet variety. The result of this choice is that (1) the leaflet spends
more time between altitude levels than did the leaflet in Example No. 1,
hence, the horizontal drift vector for any given altitude increment will
be greater for this second leaflet than for the first, assuming wind con-
ditions to be the same for both cases; and (2) the size of the ground
pattern is much tighter than it is in Example No. 1.
The winds listed in the computation form sheet are identical to
those found in Example No. 1. The procedure for making the calcula-
tions, plotting the vectors, and determining the pattern size and density
is the same as that followed in Example No. 1. The steps involved are
as follows:
(1) Find the aspect ratio in Table G-1.
(2) Determine the number of leaflets per pound in Table G-2.
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LEAFLET DESCENT
(3) Find the ground rate of descent (Vo) and type of motion
(autorotating or non-autorotating) in Table G-3,
(4) Find the variation coefficient ( RT/To ) in Table G-4.
(5)
Find the time factors for this non-autorotating leaflet, with
the Vo as determined in step 3, in Table NA-21; list these
values in the appropriate column of the computation sheet,
(6) Multiply the time factors by the corresponding wind speed
to determine the horizontal drift distance in each altitude
increment,
(7)
(8)
Plot the horizontal drift distances as vectors on the graph
paper, taking care that allowance is made for any partial
drop heights in the first and last 5000-foot increments of
the descent.
Draw the resultant horizontal drift vector from the point of
release to the point of impact, and measure the magnitude
and direction of this vector.
(9) Determine and measure the point of maximum normal devi-
ation from the net vector.
(10) Convert the measured distances of the resultant vector and
the maximum normal deviation from nautical miles to statute
miles, and list these values on the computation form.
(11) Determine the major axis of the ellipse by m(iltiplying the
magnitude of the resultant vector by the variation coefficient,
(12) Determine the minor axis by dividing the descent distance in
feet by 5280 (to obtain the descent distance in miles) and
adding to this the product of the maximum normal deviation
and the variation coefficient.
(13) Determine the area of the ground pattern from the formula
A= 4 ab where a and b are the major and minor axes,
1 Were this an autorotating leaflet rather than a non-autorotating leaf-
let, the time factors would be found in Table A-2 rather than in Table
NA- 2.
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LEAFLET DESCENT
(14) Multiply the weight of the payload by the number of leaflets
per pound to obtain the total number of leaflets released.
(15) Divide the total number of leaflets obtained in step 14 by
the area figure found in step 13 to get the average density
in leaflets per square mile.
(16) Divide the average density found in step 15 by 2800 to ob-
tain the average density in leaflets per 10, 000 square feet.
(17) Draw and shade in the ground pattern on the graph paper.
As mentioned earlier, the descent rate is slower and the varia-
tion coefficient smaller for the leaflet selected in Example No. 2 in
comparison with that in Example No. 1. Therefore, the horizontal
drift is greater, and the ground pattern is smaller. In order to reduce
the length of the drift vector to be approximately equal to that of
Example No. 1, the release height is lowered from 37, 000 to 34, 000
feet. The ground pattern is, however, little affected by this change.
It is interesting to superimpose the two problems, i. e. ,
Example Nos. 1 and 2, on the same sheet of graph paper for purposes
of comparison. This is shown on one of the following graphs.
Example No. 3 - Example No. 3 is included as a further study, al-
though there are no important differences in it from the previous two
examples. An autorotating leaflet is selected for this problem, and a
different set of wind conditions are used. The procedures for working
up the drift and ground pattern are identical to those outlined under
Example Nos. 1 and 2.
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Height Time
Wind
Horiz. Drift
Azimuth
Date June 25, 1960
Increments
Factor
Speed
Distance
Angle
Time of Launch
0600
(thsds of ft)
(hours)
(knots)
(nauti. mi.)
(deg)
Launch Site #
2
50-45
Target X
45-40
40-35
0.17
60
10.2
320
35-30
0.25
50
12. 5
300
Leaflet Data
30-25
0.26
40
10.4
280
Paper Weight
16
25-20
0.30
40
12.0
290
Size 6" x 4"
20-15
0.34
30
10.2
280
Aspect Ratio 1. 5
15-10
0.37
30
11.1
270
RT/To 0.63
10-5
0.40
10
4.0
180
Yo 3.3 ft/ sec
5-0
0.42
5
2.1
170
Autorotator
Non-autorotator
X
Leaflets/lb
487
Computations
Total horizontal drift vector from release to impact: 282?, 57 naut. mi. 66 miles
Maximum deviation normal to net vector: 8 naut. miles = 9 miles
Ground Dispersion Pattern:
Major Axis 66 x 0.63 = 41 miles
Minor Axis 37, 000 + 9 x 0.63 = 13 miles
5280
4 x 13 x 41 = 420 square miles
Payload 400 pounds
Number of leaflets 400 x 487 = 194, 800
Mean density 194, 800 + 420 = 464 leaflets/mil
Leaflets/mil + 2800 = leaflets/ 10, 000 ft2 = 464 + 2800 = 0. 16 leaflets/10, 000 ft2
-38-
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0
N
S31IW 1b011fVN
0
z
a)
1-4
W
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Height Time
Wind
Horiz. Drift
Azimuth
Date June 25, 1960
Increments
Factor
Speed
Distance
Angle
Time of Launch 0600
(thsds of ft)
(hours)
(knots)
(naut. mi.)
(deg)
Launch Site # 2
50-45
Target X
45-40
Release Altitude 34, 000 ft.
40-35
60
320
35-30
0.25
50
12. 5
300
Leaflet Data
30-25
0.30
40
12.0
280
Paper Weight 16
25-20
0.35
40
14.0
290
Size 6" x 4. 8"
20-15
0.40
30
12.0
280
Aspect Ratio 1.25
15-10
0.44
30
13.2
270
RT/.T
0.20
10-5
0.47
10
4.7
180
o
Vo 2.8 ft/ sec
5-0
0.49
5
2. 5
170
Autorotator
Non-autorotator
X
Leaflets/lb 406
Computations
Total horizontal drift vector from release to impact: 277?, 60 naut. mi. = 69 miles
Maximum deviation normal to net vector: 8 naut. miles = 9 miles
Ground Dispersion Pattern:
Major Axis 69 x 0.20 = 14 miles
Minor Axis 34, 000 + 9 x 0. 20 = 8 miles
5280
Area 4 x 14 x 8 = 88 square miles
Payload 400 pounds
Number of leaflets 400 x 406 = 162, 000
Mean density 162, 000 _ 88 = 1840 leaflets/mi2
Leaflets/mi2 _ 2800 = leaflets/10, 000 ft2 = 1840 _ 2800 = 0. 66 leaflets/10, 000 ft2
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-41-
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LEAFLET DESCENT
-42-
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Example No. 3
Height Time
Wind
Horiz. Drift
Azimuth
Date July 8, 1961
Increments
Factor
Speed
Distance
Angle
Time of Launch 1530
(thsds of ft)
(hours)
(knots)
(naut. mi.)
(deg)
Launch Site # 1
50-45
Target Y
45-40
0.29
60
17.4
290
Release Altitude 32, 000 ft.
40-35
0.33
70
23.1
270
35-30
0.38
70
26.6
260
Leaflet Data
30-25
0.43
50
20.5
240
Paper Weight
13
25-20
0.48
40
19.2
230
Size 8-1/2" x 2.
13"
20-15
0. 53
30
15.9
210
Aspect Ratio
4.00
15-10
0.59
10
5.9
330
RT/To 0.36
10-5
0.64
10
6.4
360
Vo 2.0 ft/sec
5-0
0.68
5
3.4
010
Autorotator
X
Non-autorotator
Leaflets/lb
796
Computations
Total horizontal drift vector from release to impact: 2450, 57 naut. mi. = 66 miles
Maxim,im deviation normal to net vector: 14 naut. miles = 16 miles
Ground Dispersion Pattern:
Major Axis 66 x 0. 36 = 24 miles
Minor Axis 32, 000 + 16 x 0.36 = 12 miles
5280
- x 24 x 12 = 226 square miles
4
Payload 400 pounds
Number of leaflets 400 x 796 = 318, 000
Mean density 318, 000 ' 226 = 1400 leaflets/mil
Leaflets/mil . 2800 = leaflets/10, 000 ft2 = 1400 = 2800 = 0. 50 leaflets/ 10, 000 ft2
-43-
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Balloon Delivery System
J 100
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Section I
Page
J-100 CAPABILITY
1
LOAD METHODS
4
PERFORMANCE CHARACTERISTICS
6
MATCHING LEAFLET DRIFT TO BALLOON TRAJECTORY
17
Launch Sites
17
Profiles of rise to impact
20
Example of Computation No. 1
25
Example of Computation No. 2
28
PROCEDURE FOR COMPUTATIONS
32
SPECIAL SITUATIONS
40
BALLOON DISPERSION AND LEAFLET COVERAGE
41
OPERATING INSTRUCTIONS
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J-100 BALLOON
THE J-100 BALLOON DELIVERY SYSTEM
Abstract - The J-100 meteorological balloon is used as the delivery
system for leafleting operations in the short range target areas up to
250 miles distant. The balloon with its payload rises at a fairly con-
stant rate. As it passes through regions of successively lower air
density, the gas in the balloon expands and stretches the balloon film.
Finally, the film stretches to the point of rupture and releases the pay-
load to drift down separately and disperse over the ground.
The J-100 is a versatile delivery system for these short ranges
since the distance and height of flight can be altered by varying the pay-
load-free lift combinations. These features, along with a knowledge of
wind conditions and the principles of leaflet descent and dispersion,
form the variables which are at the disposal of the operator to control
the range and burst altitude for leafleting the target area.
This section of the handbook details the performance character-
istics of the J-100 balloon, including charts, graphs and tables obtained
from actual tests. Examples show how the best payload-free lift com-
bination for a specific leafleting situation is selected, and matching
leaflet drift to the balloon trajectory so the total problem from launch
to impact is worked out.
Other considerations include launching sites, both fixed and
mobile, computing and plotting balloon trajectories, the choice of leaf-
let size and weight, and performance characteristics of the J-100 when
flying into clouds, on night flights, aged balloons, and the use of disso-
ciated ammonia for the lifting gas in place of hydrogen.
At the end of this section will be found detailed operating in-
structions for the J-100 balloon delivery system (external load)
arranged in sections covering assembly of the balloon, assembly and
loading of the carrier, inflation, hydrogen handling, and launching.
J-100 Capability - The J-100 balloon is a neoprene meterological bal-
loon. It is basically a wind sounding balloon but can be easily adapted
for load carrying purposes. The balloon film is extensible; its flaccid
diameter (i.e., the diameter before inflation) being 16 inches and the
burst diameter being in the order of 80 inches.
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A payload is attached to the balloon and the balloon is then infla-
ted with a lighter-than-air gasl to the point where the system is just in
equilibrium with the air. If now a small additional amount of gas is
added to the balloon, the system will become buoyant and, if freed, be-
gin to rise. This additional increment of gas is called the free lift, and
the rate of rise is dependent on the amount of excess gas (free lift)
imparted to the system.
The system rises at an essentially constant rate, the gas in the
balloon expanding and stretching the balloon film as the system passes
into regions of successively lower density. Finally the film is stretched
beyond its elastic limit and the balloon ruptures, releasing its payload
which drifts down separately to the target area.
In a very general way the delivery capability of the J-100 can be
summarized by the following schematic:
O
is
0
0
N lo-{
114
I 2
TIME TO BURST , HOURS
Figure 1. CAPABILITY OF J-100 BALLOON
1
Usually hydrogen is used as the lifting gas, although dissociated
ammonia and coal gas have been used successfully.
czz/ / / T //
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The shaded area bordered by the four boundary lines "fast riser,
light load, slow riser, and heavy load", represents the area into which
a J-100 can be reliably used to carry a payload. The boundary limits
chosen for this handbook are: fast riser - 500 grams free lift; light
load - 2 pounds; slow riser - 50 grams free lift; heavy load - 6 pounds.
Theoretically, any point within the boundary is attainable if the right
payload and free lift are selected. In practice, the given series of
recommended payload-free lift combinations will suffice, and for most
purposes there will be no reason to use any other than these recom-
mended values.
Referring to the schematic again, it is seen that the J-100 rep-
resents a rather versatile short range capability. It is able to deliver
a light load to an altitude of 40, 000 feet in a time period varying from
about 1 to 2-1/2 hours depending on the free lift selected, or a heavy
load to an altitude of 23, 000 feet in a time period varying from 1/2 to
1-1/2 hours. Assuming an average wind of 40 mphI from ground to
burst, the heavy load will be carried a distance from 20 to as much as
60 miles from the launch site, while the light load will be drifted from
40 to 100 miles2 before releasing its payload. If a leaflet descent time
of 2 hours is assumed for the 23, 000 foot release and 3 hours for the
40, 000 foot release altitudes3, a leaflet drift of 40 miles in the case of
the low release and 60 miles for the high release would result. A total
drift vector from balloon launch to leaflet impact would then be as fol-
lows:
DRIFT VECTORS J-100
Load
Rise
Balloon drift
Leaflet drift
Total drift
heavy
rapid
20 miles
40 miles
60 miles
heavy
slow
60
40
100
light
rapid
40
60
100
light
slow
100
60
160
1 40 mph = 35 knots, an average wind condition at altitude.
2 The distances are obtained by multiplying the time to burst by the
average wind, e. g. , 1-1/2 hours x 40 mph = 60 miles.
3 This corresponds, for example, to an autorotating leaflet with a
ground rate of descent (Vo) of 2.7 feet/second.
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Under average wind conditions and using an "average" leaflet,
it is seen that a distance of from 60 to 160 miles results. Under higher
or lower wind conditions and with a leaflet having faster or slower rate
of descent, the total distance could be easily altered to points between
50 and 250 miles, with distances on either side of this range attainable
under special conditions. In general, however, the 50 to 250 mile
range is considered to be the capability of the J-100 balloon, and for
planning purposes a target area outside of these limits should be scru-
tinized carefully for means of delivery by a carrier other than the
J-1001.
Load Methods - There are two methods of using the J-100 as a load
carrying vehicle: (1) placing the payload inside the balloon by stretch-
ing the balloon neck and inserting the load prior to inflation; (2) sus-
pending the load outside of the balloon from the balloon neck. The first
method is called internal loading, while the second is called external
loading.
Early leaflet operations with the J-100 were internal-load oper-
ations. In this case the balloon simply rises to burst, at which point
the load separates from the balloon and floats down independently. This
method, however, suffered from such serious limitations as the follow-
ing: the maximum load that could be delivered was 2 pounds; the pre-
mature burst rate2 was excessive; the inflation rate could not be in-
creased without encountering a prohibitively high premature burst rate;
and the bursting of the balloons after release was erratic. In order to
overcome these limitations, an external loading method has been devised
which simply and economically permits flying larger loads, virtually
eliminates prebursting3, allows more rapid inflation, and eliminates
erratic bursting3.
1 For targets under 50 miles a simple leaflet drift by leaflets released
from an airplane should be considered. For targets over 250 miles the
Pillow balloon might be used.
2 A "premature" burst is a balloon rupture occuring during inflation due
to a shifting and fluttering of the load which causes scoring and abrading
of the balloon during the inflation operation.
A certain amount of prebursting (of the order of 1%) is due to defective
balloons. This is also true for "erratic" bursting which is the bursting
of balloons while airborne prior to reaching the intended volume. Very
few balloons are defective in this sense, unless handled improperly.
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It is therefore recommended that the external loading system be
used rather than the internal load. The charts, graphs, and tables con-
tained in this handbook were obtained from test results using external
loads.
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J-100 BALLOON
PERFORMANCE CHARACTERISTICS OF THE J-100
The performance characteristics of the J-100 can perhaps best
be summarized by reference to four graphs.
Figure 2 shows the relationship of burst altitude to payload. It
is seen that within the range of 2 to 6 pounds, the relationship can be
represented as being linear. Release at any particular altitude between
20 and 40 thousand feet could be effected simply by choosing the appro-
priate payload from the graph and loading the balloon accordingly. It
will usually be found, however, that one of the four payloads tested (2,
3, 4, and 6 pound loads) will satisfy the requirements of the operational
situation. Nonetheless, the graph is useful in picturing how the burst
altitude is effected by load. It is interesting to note also that the spread
in the burst altitude is constant over the entire range of altitudes repor-
ted, i.e., ? 3000 feet. It might further be pointed out that burst al-
titude is essentially independent of the free lift.
Figure 3 shows the relationship of rate of rise to free lift. Here
again, the relationship is seen to be linear between the range of 100
and 500 grams of free lift. For free lifts below 100 grams, the linearity
does not appear to hold. Theoretically it would be possible to obtain
any rate of rise desired simply by matching the rate of rise to its cor-
responding free lift. Practically, one of the five free lifts tested (50,
100, 200, 350, and 500 grams) will satisfy almost any operational re-
quirement. However, the graph is useful for planning and orientation
purposes. Rate of rise is seen to be largely independent of payload.
Figure 4 is particularly interesting when it is used in combina-
tion with the previous two graphs. A family of rate of rise curves is
plotted on a graph which has "time to burst" as the ordinate and "burst
altitude" as the abscissa. The result being that if a specific time to
burst and burst altitude are desired (e. g. , 1. 5 hour air-time from
launch to burst with a release at 35, 000 feet), the required rate of rise
can be obtained directly from the graph (for the example chosen, ap-
proximately 400 feet minute). Turning to Figure 3 it is seen that a free
lift of 200 grams will yield a rate of rise of 400 feet per minute. From
Figure 2, a payload of 3 pounds will cause a burst at 35, 000 feet. A
summary of the entire flight of a balloon is therefore described in these
three graphs.
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N
2 4
PAYLOAD , LBS
1
WITHIN THE RANGE 2 TO 6 POUNDS, H= -4L + 47
WHERE: H =BURST ALTITUDE
L = PAYLOAD
NOTES:
1. DASHED LINES INDICATE EXPECTED SPREAD ABOUT THE
AVERAGE BURST ALTITUDE (? 3000 FEET) FOR 80% OF
THE BALLOONS.
Figure Z. J-100 BALLOONS: RELATIONSHIP OF
BURST ALTITUDE TO PAYLOAD
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: 500
U) 400
200 300
FREE LIFT, GRAMS
WITHIN THE RANGE 100 TO 500 GRAMS, R = 0.77F + 246
WHERE: R: RATE OF RISE
F : FREE LIFT
NOTES:
1. ARROW HEADS INDICATE FREE LIFTS TESTED.
2. X - INDICATES ACTUAL RESULTS FROM FLIGHT TESTS.
Figure 3. J-100 BALLOONS: RELATIONSHIP OF
RATE OF RISE TO FREE LIFT
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2o0
300
400
500,
600
6
4 3
2
0.5
BURST ALTITUDE , 1000s FEET
NOTE:
1. ARROW HEADS INDICATE BURST ALTITUDES
OF THE FOUR PAYLOADS TESTED.
Figure 4. AIRTIME FROM LAUNCH TO BURST FOR RATES
OF RISE OF 200 TO 600 FEET /MINUTE
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It should be pointed out that not only is it possible to start with
the desired air time and burst altitude and work back to the required
payload and free lift needed to satisfy the conditions, but the process
can be worked in reverse as well. That is, one can start with the pay-
load (say 4 pounds) and obtain the burst altitude (31, 000 feet). Then
choosing a free lift (350 grams) it is found that a rate of rise of approxi-
mately 500 feet/minute results. Going to Figure 4, for a burst altitude
of 30, 000 feet and a rate of rise of 500 feet/minute, an air time of just
over 1 hour is required.
Figure 5 is a graphical summary of the payload-free lift com-
binations tested. This graph is actually the most useful one of the four.
Not only does it report actual test results, but it is a summary of all
the pertinent information on one graph. The load and free lift are di-
rectly related to the burst altitude and air time, and conversely.
Summary
(1) Burst altitude is directly proportional to payload and inde-
pendent of free lift. A range in burst altitude from 23, 000 to
40, 000 feet results from payloads between 6 and 2 pounds.
(2) Rate of rise is directly proportional to free lift and largely
independent of payload. A range in rate of rise from 250 to
600 feet/minute results from free lifts between 50 and 500
grams.
Performance Within 5000-Ft. Levels - Performance charts, breaking
the flight up into successive 5000 feet increments, follow.
Table 1 summarizes the flight results for the various load and
free lift conditions tested, showing the burst altitude, the rate of rise,
the time to burst (in hours), and the time spent between altitude levels
(also in hours). The time spent between successive 5000-foot altitude
levels is the distinctive information presented in this table. This incre-
mental break down of time is vital for working up balloon trajectories,
and, once the operator familiarizes himself with the general character-
istics of the J-100, Table 1 should be used almost exclusively for work-
ing up detailed flight trajectories.
Table 2 presents time to burst in minutes, and rate of rise
between successive 5000-foot altitudes is reported in place of the time.
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O
0
o a o
O Q
O
Z p J 0
D Z
0
Z
d O
?
N a
0a 0
to
a Z
0
O
0
0
0
0
N
0
it)
M
0
M
N
\1
O
O sun)
0
0 0 0
M N
1333 90001 ` 3ofllllld lsans
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Table 1. J-100 Performance Table
Incremental Time Factors
J-100 DAYTIME FLIGHTS
Free Lift Burst Rate of Rise Time to
(Grams) Altitude (ft/min) Burst (hours)
50 40, 000 260 2. 59
100 40,000 340 1.95
2 Pound Load 200 40, 000 440 1. 52
3 50 40, 000 560 1, 19
500 40,000 650 1.03
50 35, 000 230 2. 51
100 35, 000 320 1.84
3 Pound Load 200 35,000 400 1.45
350 35, 000 510 1.14
500 3 5, 000 630 0.92
200 31,000 400 1.30
4 Pound Load 350 31,000 500 1.03
500 31,000 560 0.92
6 Pound Load 200 23, 000 370
3 Pound Load 200 35, 000 330
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Table 1. J-100 Performance Table
Incremental Time Factors
J-100 DAYTIME FLIGHTS
Time Spent Between Altitude Levels (hours)
0-5
5-10
10-15
15-20
20-25
25-30
30-35
35-40
0.42
0.38
0.36
0.33
0.31
0.29
0.26
0, 24
0.24
0.28
0.27
0.25
0.24
0.23
0.23
0.21
0.19
0.21
0.20
0.20
0.19
0.18
0.18
0.17
0.14
0.16
0.16
0.15
0.15
0.15
0.14
0.14
0.10
0.13
0.14
0.14
0.13
0.13
0.13
0.13
0.44
0.42
0.38
0.36
0.33
0.30
0.28
0.30
0.29
0.27
0.26
0.25
0.24
0.23
0.21
0.21
0.22
0.21
0.21
0.20
0.19
0.16
0.18
0.17
0.17
0.16
0.15
0.15
0.11
0.13
0.14
0.14
0.14
0.13
0.13
0.21
0.21
0.22
0.21
0.21
0.20
0.04
0.16
0.17
0.17
0.17
0.17
0.16
0.03
0.14
0.16
0.15
0.15
0.15
0.14
0.03
0.21
0.22
0.23
0.23
0.15
J-100 NIGHT-TIME FLIGHTS
0.24
0.26
0.27 0.26 0.26 0.26
0.24
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Table 2. J-100 Performance Table
Incremental Rates of Rise
J-100 DAYTIME FLIGHTS
Free Lift Burst Rate of Rise Time to
(Grams) Altitude (ft/min) Burst (min)
50 40,000 260 155
100 40,000 340 117
2 Pound Load 200 40, 000 440 91
3 50 40,000 560 71
500 40,000 650 62
50 3 5, 000 230 150
100 35,000 320 110
3 Pound Load 200 3 5, 000 400 87
350 35, 000 510 68
500 3 5, 000 630 55
200 31,000 400 78
4 Pound Load 3 50 31, 000 500 62
500 31,000 560 53
6 Pound Load 200 23, 000 370
3 Pound Load 200 35, 000 330
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Table 2. J-100 Performance Table
Incremental Rates of Rise
J-100 DAYTIME FLIGHTS
Incremental Rate of Rise (ft/min)
0-5
5-10
10-15
15-20
20-25
25-30
30-35
35-40
200
220
230
250
270
290
320
340
340
300
310
330
340
360
370
390
440
400
410
420
430
450
470
500
580
520
530
540
550
560
580
590
800
650
610
610
620
630
640
640
190
200
220
230
250
280
300
280
290
300
310
320
340
360
400
400
380
390
400
410
430
520
470
480
500
520
540
560
7 50
640
580
600
610
620
630
400
390
380
390
400
420
440
520
480
480
480
500
530
560
600
530
540
550
560
580
600
400
380
370
370
370
J-100 NIGHT-TIME FLIGHTS
350
330
310 320 320 340
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J-100 BALLOON
MATCHING LEAFLET DRIFT TO BALLOON TRAJECTORY
To bring a balloon to a point in space is a useful accomplish-
ment. However, it is not nearly so meaningful as to match a leaflet
drift to a balloon trajectory such that the total problem from launch to
impact is worked out. Since the balloon's trajectory begins at the
launching site, a consideration of the types of launching possibilities is
in order before taking up examples of the entire problem from launch
to impact.
There are three distinct types of launching possibilities:
(1)
(2)
(3)
Launching from a single fixed site
Launching from the best suited one of several fixed sites
Launching from a mobile unit which could be either land-
based or ship-based.
Mobile Launch Site - The most adaptable type of launch is, of course,
the mobile unit. This is particularly true for the ship-based operation
which can range up and down the coast and closer or further away from
the target as the case may require, all the time in a very nearly ready
state to launch. The land-based mobile site will not have as much
flexibility in choosing its launching site and may have to contend with
certain environmental factors (such as a curious populace) as well.
Also, the setup time will usually be longer than for the ship-based
launch.
Both wind direction and magnitude are important for a mobile
launch; however, if the magnitude is greater or less than can be con-
veniently compensated by altering the payload and free lift to suitl, a
change in distance between the launch site and target can readily be
effected instead. Likewise, a change in position can be made to take
best advantage of the wind direction.
I This might occur in cases where the leaflet carriers were preloaded
and it would not be easy to alter the payload quickly.
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Figure 6. MOBILE LAUNCH UNIT AFFORDS DISTANCE
AND DIRECTIONAL ADAPTABILITY
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0
SITE 4 ^
O
Figure 7. MULTIPLE LAUNCH SITES AFFORD
DIRECTIONAL ADAPTABILITY
Multiple Fixed Launching Site - The next most adaptable arrangement
is the multiple fixed site situation. The most common setup here is to
have a series of sites strung out along the border but not appreciably
set back from it. Directional versatility results from such an arrange-
ment, with distance flexibility dependent upon intelligent choice of the
payload, free lift, and leaflet.
Single Fixed Launching Site - Launching from a single fixed site is, of
course, the most difficult problem. It is somewhat eased, however, if
there is more than one target as is almost always the case. High winds
can be used for the longer-distance targets, while low winds can be
used for those nearer. Directionally, as long as the wind is blowing in-
to the target area, a suitable target can probably be found. Moreover,
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the problem is not quite as severe as it may first appear since both the
distance and direction may be altered, within limits, by selection of the
most appropriate payload (which determines the burst altitude) and free
lift (which controls rate of rise and therefore time to burst). This is
illustrated by Figures 5 through 9, in which the leaflet characteristics
are held constant, the purpose being only to show how a distance-direc-
tional versatility exists by using the balloon alone. Changing the leaflet
would change the air time from release to impact and, consequently,
the drift distance. The direction, however, would be virtually unaf-
fected. Since the leaflet will usually be fixed well ahead of launch, al-
teration in the leaflet is not a real possibility for any given mission.
Therefore, to emphasize achieving flexibility through change of the pay-
load and/or free lift is more realistic.
Figure 8 is a profile of the balloon rise to burst followed by the
leaflet descent to impact. The burst altitude is held constant, and
therefore the difference in the distance from launch to impact is seen
to be solely a result of the longer or shorter time the balloon takes to
reach the release altitude, depending on the free lift imparted to the
system.
Figure 9 is again a profile of the balloon rise to burst followed
by the leaflet descent to impact. Here, however, the rate of rise is
held constant and the payload is varied. The balloon with the lighter
load, of course, bursts at a higher altitude, resulting in, a greater
distance from launch to impact.
Figure 10 is a top view of the profile shown in Figure 8. The
result is a difference in distance with no change in direction.
Figure 11 is a top view of the profile shown in Figure 9. It is
seen here that due to the small amount of shear between the two release
altitudes (in this case about 70), not only does a difference in distance
result, but also a small change in direction.
Figure 1Z is also a top view of the profile shown in Figure 9. A
change in wind direction between the two release altitudes of 300 was
selected for this example. This results in a significant change in over-
all direction. In addition, of course, the higher burst altitude yields a
longer distance from launch to center of impact.
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I = FAST RISER
2 = AVERAGE RISER
3 = SLOW RISER
Figure 8. RATE OF RISE PROFILE
or
DRIFT
Figure 9. RELEASE ALTITUDE PROFILE
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OR
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Z
X:
x
W
V
0
W
J
J
J
~~
Q
Q
to
J
0
Z
J
Q
=
p
W
CD
F-
=
F-
to
n
0
a
-
N
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01
w
W
Z J
w 0 LL U) U)
U) O Q
w w J
Q J ww WJ
0 m u
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(1) The slower the rate of rise, the longer the distance from
launch to burst (and consequently impact).
(2) The smaller the payload the higher the burst altitude and
consequently the longer the distance from launch site to
point of burst and center of impact. (An exception would
occur when there is a reversal in the winds in the higher
altitudes. This is most unlikely for the great majority of
cases, however.)
(3) When there is wind shear, a difference in release altitude
will alter the direction. A difference in rate of rise, how-
ever, leaves the direction unaffected.
The launching possibilities described above apply to the multiple
site and mobile unit launches as well. They are less critical for these,
however, and therefore the examples which follow will be for the most
difficult case, the single fixed site. Application of the method to the
other two cases should be obvious.
Example 1 - As a first example, assume that an autorotating leaflet has
been selected with a ground rate of descent (Vo) of 1.4 feet/second, as-
pect ratio of 2.75, length of 6 inches, and a paper weight of 16 pounds;
and that the leaflets have been printed up and delivered to the site await-
ing appropriate winds. It will be noted that this particular leaflet is a
long air-time leaflet (see Leaflet Table A-1) and therefore suited to a
long-distance drift. It is assumed that the choice was made deliberate-
ly, the target being 210 nautical miles from the fixed site at an angle of
700 measured from due Northl.
A computation form sheet corresponding to that which has been
provided for working up leaflet drift is needed for working up balloon
trajectories also.
The first step is to fill in the wind speeds and directions re-
ported for each 5000-foot increment. This is done both on the balloon
and leaflet computation form sheets.
1 This corresponds to a wind blowing from 70? plus 180? or 250?
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The next thing is to work up the leaflet drift, starting from the
target and working it back in space. This is done by computing the
horizontal drift distance in each 5000-foot altitude increment (by mul-
tiplying the time factors, in this case found in Table A-2, by the cor-
responding wind speed). Starting with the altitude increment 5-0 and
proceding on up through 40-35, the successive drift vectors are plotted
out, the head of the 5-0 vector being on the target and the subsequent
vectors being laid out with their heads at the tail of the preceding one:
TARGET
I0
Figure 13. LEAFLET DRIFT VECTORS
If the target and the launch site have been connected by a straight
line (that is, the vector of length 210 nautical miles at an angle of 70?
measured from due north) on the same plot that the leaflet drift is
worked up on, it is possible to roughly gauge the best release altitudes.
The criterion for judging is this: the further any point on the drift vec-
tor is away from the line connecting target to launch site, the less at-
tractive is that particular altitude level for leaflet release. The reason
for this rule is that, again roughly speaking, the resultant balloon vec-
tor from launch to burst will have very nearly the same azimuth (i. e, ,
direction) as will the resultant leaflet drift vector. So if a release alti-
tude is selected which has its vector tail close to the launch-target con-
necting line, substantial target coverage will result.
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In this example, release at either 30 or 35 thousand feet would
ensure reasonable coverage, while the 40 thousand foot vector strays
too far away from the connecting line. It would therefore be prudent
to select either the 3-pound load (35, 000-foot burst) or the 4-pound
load (31, 000-foot burst). But in order to make the choice it is neces-
sary to consider the distances involved. Measuring from the launch
site to these two possible release altitudes finds the 35, 000-foot point
just under 80 nautical miles from the site, and the 31, 000-foot point
about 100 nautical miles from the site. Looking now at the wind speeds
and direction, it is seen that the winds in the 15-35 thousand foot levels
are the only winds which have their direction primarily in the intended
distance of travel. Moreover, the wind speeds in the lower altitudes
are low enough in this case so as not to materially alter the situation
if the 15-35 level is selected for particular emphasis. Focusing atten-
tion on the 15-35 winds then, it is seen that the average wind speed
from 15-30 is 47 knots while from 15-35 it is 48 knots. The balloon
then would have to spend over 2 hours (2 x 47 = 94 knots) in the 15-30
level to traverse the necessary 100 miles, while it would only have to
spend slightly less than 1-1/2 hours (1. 5 x 48 = 72 knots) in the 15-35
thousand foot level. Obviously the latter altitude level is the correct
choice, and the 3-pound load is therefore the payload to fly.
Now the free lift must be selected. Focusing again on the 15-35
thousand foot levels, it is seen from J-100 Table 1 that only the 50-
gram free lift will allow the balloon to remain at these altitudes for any-
where near 1-1 /2 hours (50 grams of free lift will keep the balloon in
these altitudes for 1. 27 hours, while 100 grams of free lift reduce
this to 0. 98 hours). The choice is easily made then to fly a 3-pound
load with 50 grams of free lift.
Returning to the balloon computation form sheet, the time factors
are filled in for this payload - free lift combination and the horizontal
drift distance computated for each altitude increment by multiplying the
time factor by the corresponding wind speed.
This done, the balloon trajectory may be plotted. 1 Plotted out
it is found that the balloon will burst at a distance of 65 nautical miles
from the launch site and at an angle of about 700 from true north.
1 It is suggested that this be done on a fresh map, piece of graph paper,
or overlay, rather than on the same sheet the leaflet descent vectors
were worked on.
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Now the leaflet drift vector may be added to the balloon drift to
find the center of impact. Rather than re-plot the entire leaflet descent
for the various levels, it is easier to measure the distance and direc-
tion of the resultant leaflet drift vector and draw it in. In this case, the
resultant is 132 nautical miles at an angle of 253? (73? from true north).
The overall distance from launch to impact is therefore 195 nautical
miles at an angle of 720 from true north.
By working up the ground pattern dimensions from the incremen-
tal plot of the leaflet drift vectors and according to the instructions in
the Chapter on Leaflet Release Specifications, it is found that an ellipse
with major axis of 34 nautical miles (39 statute miles) results. Draw-
ing this in, it is seen that the target will largely be covered although
the center of impact will be somewhat short of the target center.
Example 2 - As a second example, assume that a non-auto rotating leaf-
let with a ground rate of descent of 3.0 feet/second, length of 8-1/2
inches, aspect ratio of 1. 50, and paper weight of 13 pounds has been
selected. It will be noted that this represents a medium-fast descend-
ing leaflet and is therefore most appropriate for reasonably close tar-
gets. Assume that the target meets this requirement of proximity, it
being 105 nautical miles from the fixed site. The azimuth is 130? from
true north
l.
The winds are recorded on the J-100 computation Form Sheet
and the Leaflet Form Sheet. The procedure for making the calculations,
plotting the vectors, selecting the payload and free lift, and determin-
ing the pattern size are as follows:
(1)
Follow steps 1-6 as described in the Section entitled Leaf-
let Descent and Dispersion which covers recording of the
leaflet characteristics and computing the horizontal drift
in each altitude increment.
(2) Plot the horizontal drift vectors on the graph paper, start-
ing from the target (the 5-0 vector) and working back to
altitude (ending with the 40-35 vector).
(3) It is seen that for this example the closest approach to the
target-launch site connecting line are the drift vectors be-
tween the 35 and 25-thousand foot altitudes. The choice is
1 Corresponding to a wind blowing from 130? + 180?, = 310?
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therefore between the three-pound load (35, 000-foot burst),
the four-pound load (31, 000-foot burst) and the six pound
load (23, 000-foot burst).
(4) Measure the distance from launch to burst for the three
possible burst altitudes. This turns out to be 40, 47, and
71 nautical miles for the three burst altitudes of 35, 31,
and 23 thousand feet, respectively. As most of the balloon
drift in the direction of the target will be in the altitudes
above 15 thousand feet (the average winds here being about
50 knots), it is on this part of the flight that attention must
be focused as far as selection of the payload and free lift is
concerned. For the six-pound load, the balloon would have
to spend about 1-1/2 hours (1-1/2 x 50 = 75) in the 15-23
thousand foot levels to get the necessary distance; the four-
pound load would need to spend just 1 hour (1 x 50 = 50) in
the 15-31 thousand foot levels to drift the needed distance;
and the three-pound load would require just over 3/4 of an
hour (3/4 x 50 = 37) to drift the needed distance.
(5)
Looking to the J-100 Performance Tables it is seen that the
six-pound load falls far short of the required time, the four-
pound load falls somewhat short, and the three-pound load
with 200 grams of free lift yields just the necessary time.
(6) Fill in the time factors for the three-pound load, 200-gram
free lift combination on the balloon computation form sheet,
and compute the balloon drift for each successive altitude
increment.
(7)
(8)
Plot the balloon trajectory on a new sheet of graph paper,
and measure the resultant balloon vector from launch to
burst (in this case 44 nautical miles at 3130) and record this
value on the balloon computation form sheet.
Measure the leaflet net drift vector and azimuth from re-
lease to impact (66 nautical miles - 312?), and lay out this
vector from the point of balloon burst on the new graph
paper.
-29-
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(9) Measure the maximum deviation of the leaflet drift normal
to the net drift vector (8. 5 nautical miles), and record this
value together with the leaflet net drift vector on the leaflet
computation form sheet.
(10) Compute the major axis and minor axis of the ground pat-
tern ellipse (major axis = 20 nautical miles, minor axis=
9 nautical miles), and draw the impact area in with the
center of the ellipse at the point of impact. It is seen that
the target is partly but not completely covered by the leaf-
let pattern.
To recapitulate the entire J-100 balloons - leaflet drift problem,
the procedures involved are as follows:
The leaflet size and weight are selected on the basis of the
air time2 desired, what dispersion is wanted, and how much space is
needed to print the leaflet message.
Generally speaking, leaflets with a long air-time are those
which have a ground rate of descent (V ) of 2. 0 feet/second or less. 0 This corresponds to the autorotating type of leaflet. Leaflets with a
medium air time are those with a ground rate of descent (Vo) between
2.0 and 3.0 feet/second. Many non-autorotators and a few autorota-
tors fall in this category. Finally, a short air time results from leaf-
lets with a ground rate of descent (Vo) of 3.0 feet/ second and greater.
Only non-autorotating leaflets fall in this category.
Knowing generally what rate of descent and leaflet size and
weight are desired, a particular leaflet possessing the desired charac-
teristics can be quickly selected by reference to the Leaflet Drift and
Dispersion instructions. Table G-3 lists the ground rate of descent for
Drift distance is equal to the product of the wind velocity and the air
time. Holding wind velocity constant then, a long drift distance will
result from a long air time and a short drift from a short air time.
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various leaflet sizes and weights and distinguishes between autorota-
tors and non-autorotators as well. Table G-4 lists the variation coef-
ficient (RT/To) for each leaflet size and weight combination, and,
consequently, the desired dispersion can be selected as well. A rea-
sonably tight leaflet pattern results from a coefficient of variation of
less than 0. 40, and a broad dispersion results from a coefficient grea-
ter than 0.40.
In actual practice, the size-weight-air time-dispersion
characteristics will have to be compromised somewhat in order to
choose the optimum leaflet. As long as the general requirements of
each is satisfied, howeverl, the problem can be solved.
Once the leaflet is selected, the characteristics are re-
corded on the leaflet computation form sheet.
B. Obtain the Forecast of the Winds
As pointed out earlier, the meteorological problems of
forecasting are outside the scope of this handbook. It should be obvi-
ous, however, that good, accurate forecasting is essential. To attempt
to conduct a controlled leafleting operation without this knowledge of the
winds is a waste of time and effort. It is presumed throughout this
handbook that provision for the meteorological problem is made. The
forecast winds are recorded both on the leaflet computation as well as
the balloon computation form sheet.
C, D, E, and F are combined in a stepwise procedure as each
succeeding step is related to those preceeding. The procedures in-
volved are:
C. Work out the leaflet drift (steps 1-4)
D. Select the balloon payload and free lift (steps 5-8)
E. Work up the balloon trajectory, and affix the net leaflet
drift vector to the point of balloon burst (steps 9-11)
F. Compute the ground pattern dimensions, and draw in the
ellipse (steps 12-13)
1
Usually this will not be a serious problem as there will be a choice
between several possible leaflets for most every requirement.
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(1)
List on the leaflet computation form sheet the appropriate
time factors for the leaflet selected as found in Table A-2
or NA-2 depending on whether the leaflet is an autorotaror
or non-autorotaror.
(2) Compute the horizontal drift distance for each altitude in-
crement by multiplying the wind speed by the time factor.
(3) Starting from the target, plot the horizontal drift vectors
from the ground back to altitude.
(4) Find the points of closest approach of the leaflet drift vec-
tors to the line connecting the launch site and target. If
these points are in the 23, 000 to 40, 000 foot levels, they
represent possible release altitudes for the leaflets.
(5) Measure the distances from the launch site to the possible
release levels found in step 4.
(6) Compute the average wind in the direction of the target
(these might be called the "primary" winds), and calculate
the amount of time the balloon would have to spend in the
altitudes of the primary winds for each of the distances
measured in step 5. (It might be useful to recall here that:
distance : primary wind = time required.)
(7)
Looking to the J-100 Performance Tables, select that com-
bination of load and free lift which gives: (a) a desired re-
lease altitude as found in step 4 and (b) a corresponding
necessary air time to achieve the necessary flight distance
as computed in step 6.
(8) Record the time factors for the load and free lift combina-
tion selected on the balloon computation form sheet, and
compute the balloon drift for each successive altitude incre-
ment.
(9) Plot the balloon trajectory on a new sheet of graph paper,
beginning, of course, with the launch site and ending with
burst.
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(10) Measure the distance and azimuth of the net leaflet drift
vector from release altitude to impact and lay out this vec-
tor with the tail being at the point of balloon burst and the
head being the actual center of impact.
(11) Measure the maximum deviation normal to the net drift
vector (as found on the first plot of the leaflet drift), and
record this value together with that of the net leaflet drift
vector (as found in step 10) on the leaflet computation form
sheet.
(12) Compute the length of the major axis and minor axis of the
ground pattern ellipse. Calculate the mean leaflet density.
(13) Draw out the size of the impact area as computed in step
12. The center of the ellipse is the center of impact.
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Example No. 1
BALLOON COMPUTATION FORM SHEET
Date July 26, 1960
Launch site 1
Time of launch 0700
Target U
Height
Increments
(thsds of ft)
Time
Factor
(hours)
Wind
Speed
(knots)
Horiz. Drift
Distance
(naut. mi.)
Azimuth
Angle
(degree)
45-50
40-45
35-40
40
270
30-35
0.28
50
14.0
260
25-30
0.30
60
18.0
270
20 - 2 5
0.33
50
16.5
280
15.20
0.36
30
10.8
270
10-15
0.38
20
7.6
200
5-10
0.42
20
8.4
190
0-5
0.44
10
4.4
180
Payload 3 pounds Burst altitude 3 5, 000
Free lift 50 grams Rate of rise 230 ft/min
Total load launched 1200 pounds
Total horizontal drift vector, launch to burst 65 naut.
mi. , 2500
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Example No. 1
Height Time
Wind Horiz.Drift Azimuth
Date July 26, 1960
Increments Factor
Speed Distance Angle
Time of launch 0700
(thsds of ft) (hours)
(knots) (naut.mi.) (degree)
Launch site 1
Target U
50-45
Release altitude
45-40
35, 000 ft
40-35
0.47
40
18.8
270
35-30
0.54
50
27.0
260
Leaflet Data
30-25
0.61
60
36.6
270
Paper weight 16
25-20
0.69
50
34.5
280
Size 6" x 2.1811
20-15
0.76
30
22.8
270
Aspect ratio 2.75
15-10
0.84
20
16.8
200
RT/To 0.26
10-5
0.91
20
18.2
190
V 1.4 ft/sec
5-0
0.97
10
9.7
180
Autorotator X
Non-autorotator
Leaflets/lb 893
Computations
Total horizontal drift vector from release to
Maximum deviation normal to net vector:
Ground Dispersion Pattern:
impact: 2530, 132 naut. mi.
3 5 naut. miles
Major Axis 132 x 0.26: 34 naut. mi. = 39 statute miles
Minor Axis
3 5, 000
5280 + 3 5 x 0.26: 16 naut. mi. = 18
statute miles
V x 39 x 18 : 550 square miles
4
Payload 1200 pounds
Number of leaflets 1200 x 893 = 1, 070, 000
Mean density 1, 070, 000 = 550 = 2000 leaflets /mi2
Leaflets /mi' = 2800 : leaflets/10, 000 ft2 : 2000 = 2800 0.71
leaflets/ 10, 000 ft2
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Example No. 2
BALLOON COMPUTATION FORM SHEET
Date October 3, 1962
Launch site # 1
Time of launch
1200
Target
Y
Height
Increments
(thsds of ft)
Time
Factor
(hours)
Wind
Speed
(knots)
Horiz. Drift
Distance
(naut. mi.)
Azimuth
Angle
(degree)
45-50
40-45
35-40
40
320
30-35
0. 19
40
7.6
310
25-30
0.20
60
12.0
310
20-25
0.21
50
10.5
300
15-20
0.21
40
8.4
300
10-15
0.22
20
4.4
350
5-10
0.21
10
2. 1
360
0-5
0.21
0
-
-
Payload 3 pounds Burst altitude 35, 000
Free lift 200 grams Rate of rise 400 ft/min
No. of balloons launched 550
Total load launched 1650 pounds
Total horizontal drift vector, launch to burst 44 naut.
mi., 31
-38-
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Example No. 2
Height
Time
Wind
Horiz.Drift Azimuth
Date October 3, 1962
Increments
Factor
Speed
Distance
Angle
Time of launch 1200
(thsds of ft)
(hours)
(knots)
(naut. mi.)
(degree)
Launch site # 1
Target Y
50-45
Release altitude
45-40
3 5, 000 ft
40-35
0.19
40
7.6
320
35-30
0.24
40
9.6
310
Leaflet Data
30-25
0.28
60
16.8
310
Paper weight 13
25-20
0.33
50
16.5
300
Size 8-1/2" x 5.67
20-15
0.37
40
14.8
300
Aspect ratio 1. 50
15-10
0.41
20
8.2
350
RT/To 0.31
10-5
0.44
10
4.4
360
V0 3.0 ft/sec
5-0
0.46
-
-
-
Autorotator
Non-autorotator X
Leaflets/lb 299
Computations
Total horizontal drift vector from release to impact: 3120, 66 naut. mi.
Maximum deviation normal to net vector: 8. 5 naut. miles
Ground Dispersion Pattern:
Major Axis 66 x 0.31 = 20 naut. mi. : 24 statute miles
Minor Axis 35, 000
+8.5 x 0.31 : 9 naut. mi. = 10 statute miles
5280
Area ,r
4 x 24 x 10 190 square miles
Payload 1650 pounds
Number of leaflets 1650 x 299 = 493, 000
Mean density 493, 000 : 190 2590 le lets/mi2
Leaflets/mi2 - 2800: leaflets/10, 000 ft = 2590 : 2800 : 0. 92
leaflets/10, 000 ft2
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J-100 SPECIAL SITUATIONS
Several minor problems remain to be covered on the perform-
ance characteristics of the J-100; namely, flying into clouds, night
flights, aged balloons, and use of dissociated ammonia for the lifting
gas. These are discussed below.
Flying into Clouds - There is no important change in balloon perform-
ance for daytime flights in cloudy weather. The initial rate of rise is
usually somewhat reduced, but the rate of rise during the latter part of
the flight generally increases to yield an average rate of rise identical
to that of a flight in clear sky.
Night Flights - There is no change in the burst altitude. The rate of
rise is about 20 percent less than for daytime flights, therefore, the
time spent between altitude levels should be multiplied by 1. 2 to get
the corrected time.
Aging - Balloons less than a year old do not exhibit any significant
change in performance due to aging. For balloons over a year old,
the process of crystallization becomes serious, and the film under-
goes a stiffening and decrease in extensibility. The film may be re-
conditioned by immersing it in hot water (200?F) for several minutes.
The reconditioned balloon should be suitable for use for over a month
after the heating.
Use of Dissociated Ammonia - The burst altitude and rate of rise are
about 20 percent less when dissociated ammonia is used for the lifting
gas in place of hydrogen. The net result is that, while the bursting
altitude is reduced, the total air time is unchanged.
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J-100 BALLOON
BALLOON DISPERSION AND LEAFLET COVERAGE
Generally speaking, the J-100 can be expected to burst within
+ 3000 feet of the reported burst altitude and to rise at a rate within
? 5 percent of the reported rate of rise. The result is that, rather than
having a single point release, as is assumed in all of the example prob-
lems worked out, a variety of point releases actually develop. This
tends to increase the leaflet spread beyond that described in the exam-
ples cited and consequently a lower leaflet density also results. The
magnitude of the difference is shown schematically below:
a
0
0
0
20
W
0
D
I-
I-
Q 10
3 POUND LOAD
200 GRAMS FREE LIFT
I I 1
1 /2 I 1 1/2
TIME TO BURST , HOURS
Figure 18. ZONE OF MULTIPLE RELEASE POINTS
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It is seen that, for a slow riser, high burster, the time to burst
may be increased by as much as 15 minutes; while for the low burster,
fast riser, the time is 15 minutes less than the average. For an aver-
age wind at altitude of 40 knots, this will bring the far-bursting balloons
some 10 nautical miles beyond the average release point, while the
closer burster will be 10 nautical miles short of the average. The
major axis of an ellipse calculated on the basis of a point release at 30
nautical miles must therefore be increased to 50 nautical miles (al-
though the majority of the leaflets will probably be found within an axis
length of 40 nautical miles).
Furthermore, variations in the wind speed and direction will
probably occur while the launching is in progress. This will tend to
increase the size of the ground pattern and decrease the leaflet density
by spreading out the balloon bursts over a greater area. A variation of
3 degrees on both sides of the average wind vector would, for a bal-
loon bursting 60 nautical miles from the launch site, cause a release
variation of 3 nautical miles on either side of the average.
The minor axis of an ellipse calculated on the basis of a point
release at 10 nautical miles should therefore be increased to 16 nauti-
cal miles (although the majority of the leaflets would be found within 13
nautical miles).
It might be taken as a general rule that the actual coverage will
exceed the calculated coverage from a point release by about 30 per-
cent in both the length and width of the ground pattern. This in turn
yields an area 70 percent greater than the single point release (1. 3 x
1.3 = 1.69).
There is sometimes a tendency to use several payload-free lift
combinations during the same mission in the hope of more effectively
leafleting a target area. Except for very large missions this is prob-
ably inadvisable since the actual result will be a leaflet density so low
that nowhere will there be a significant return, the leaflets being so
widely scattered as to discourage any effort to find them. If the opera-
tor realizes that he has built into the system an inherent feature in this
tendency toward spread discussed above, he should be less anxious to
increase this still more, but rather should concentrate on adequate
coverage of a single area on each specific mission.
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BALLOON DELIVERY SYSTEM
J-100
(External Load)
OPERATING INSTRUCTIONS
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Operating Instructions
for
BALLOON DELIVERY SYSTEM J-100
(EXTERNAL LOAD)
This relatively simple system will deliver a payload varying
from 2 to 6 pounds of leaflets at free lifts varying from 50 to 500 grams.
A leafleting range from 50 to 250 miles is considered to be the capabil-
ity of the J-100.
The instructions which follow are to guide you in the prepara-
tion of the J-100 System for launching. They should be followed
exactly in step-by-step sequence for a successful flight. The steps
are numbered serially and should be performed in the indicated order,
particularly within each section.
Section 1 (Steps 1 to 5) describes the assembly of the balloon.
Section 2 (Steps 6 to 9) gives directions for the assembly and
loading of the leaflet carrier.
Section 3 (Steps 10 to 13) deals with the inflation of the balloon.
Section 4 (Step 14) gives final directions for launching.
Section 5 is concerned with the handling of hydrogen.
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J-100 BALLOON
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ASSEMBLY OF BALLOON
THE J-100, before assembly,
consists of the neoprene bal-
loon, the polyethylene ring,
and the polyethylene closure.
A cap is provided (shown in
the right foreground attached
to the closure) which can be
readily snapped onto the clo-
sure or removed therefrom.
SLIDE the ring over the
neck of the balloon, as
shown.
FOLD the balloon neck
back over the ring, as
shown.
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J-100 BALLOON
STEP 4.
FIT THE CLOSURE over
the ring and folded-back
skin of balloon, as shown,
and snap the closure into
place.
Insert a length of string
through the two clearly
visible load suspension
hooks which are attached
to the closure, and pull
to make sure that the clo-
sure is snapped securely
in place. When the fit is
tight, remove this string.
REMOVE the cap from
the inflation opening, as
shown.
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ASSEMBLY AND LOADING OF CARRIER
THE TWO CARDBOARD
pieces of the leaflet
carrier, with load sus-
pension strings attached,
are shown as received.
Note the slots in these
two pieces.
Fold the larger piece of
cardboard along the two
bend lines. Fold the
smaller, rectangular
piece of cardboard along
the one bend line to form
a small lip.
ASSEMBLE the carrier
by inserting the rectangu-
lar piece of cardboard
into the slots in the folded
larger piece. The carrier
is shown completely as-
sembled, and the small
lip along the backside of
the base is clearly visi-
ble. This lip is necessary
to prevent loss of the load
during severe oscillations
of the carrier.
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LOAD the leaflets in the
carrier. The carrier is
shown partially loaded.
SUSPEND the loaded
carrier from the closure
by inserting the suspen-
sion strings through the
load suspension hooks as
shown.
Attach the appropriate
free-lift weight to the
carrier.
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INSERT THE inflation
nozzle into the inflation
opening of the closure.
This is simply a friction
fit. The inflation nozzle
is shown about to be in-
serted into the opening
and, also, after inser-
tion is complete.
Note the electrical ground-
ing of the inflation nozzle
shown in both pictures.
This safety precaution is
essential when using flam-
mable gas such as hydrogen.
THE balloon should be in
the inflation shield during
inflation if this operation
is conducted outdoors. The
balloon is shown as inflation
is about to begin.
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REGULATE THE flow of
gas from the cylinder into
the balloon by means of the
foot-operated valve. Gas
flow can be fairly rapid,
but violent fluttering of the
tubing should be avoided.
The balloon as shown, re-
quires no attention once
sufficient gas has been in-
troduced to support it.
ADD GAS SLOWLY when the
balloon begins to pick up the
load prior to equilibrium.
The balloon is shown just
beginning to pick up the load
prior to equilibrium.
Stop adding gas once the
balloon is in equilibrium,
i. e. , when it supports the
load. Exercise caution to
prevent over-inflation.
Remove the inflation nozzle
from the inflation opening,
and immediately press the
cap securely over the infla-
tion opening.
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LAUNCH the balloon by
removing the free-lift
weight. The balloon is
shown just prior to re-
lease.
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Hydrogen can be very dangerous if not handled properly. An
air-hydrogen mixture containing between 7 and 72 percent hydrogen
by volume is explosive, and in the higher ranges will burn vigorously.
On the other hand, as long as air is excluded from mixing with the
hydrogen, and no flames, sparks, or hot surfaces in excess of 400?F
are permitted near the gas, there is no danger.
SMOKING MUST NOT BE ALLOWED
in the area when using hydrogen. To minimize the chances of gener-
ating static sparks during inflation, the
HYDROGEN CYLINDER AND INFLATION NOZZLE
MUST BE ELECTRICALLY GROUNDED.
Immediate capping of the inflation opening after removal of the
inflation nozzle will minimize the introduction of air into the balloon.
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Balloon Delivery System
170 F
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Section 1.
LEAFLET CONTAINER PREPARATION
Section 2.
BALLAST PREPARATION
Section 3.
CHECK-OUT AND PREPARATION OF INSTRUMENT SYSTEM
CIRCUITS
Section 4.
RIGGING, INFLATION AND CAP INSTALLATION
Section 5.
LAYOUT OF BALLOON AND EQUIPMENT
Section 6.
INFLATION OF BALLOON
Section 7.
HYDROGEN HANDLING
Section 8.
LAUNCHING
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Operating Instructions
for
BALLOON DELIVERY SYSTEM 170F
This system has been very carefully designed to deliver a payload of 88
pounds (40 kilograms) of leaflets. The leaflets can be dropped in any one
of several selected patterns. In case of failure of the balloon to operate
as desired, emergency measures have been provided which will insure
spreading of the payload over a wide area even if it is not the one selected.
The success of any balloon flight depends mainly upon careful prepara-
tion and launching after study of meteorological conditions which will
govern flight. The instructions which follow are to guide you in the pre-
paration of the 170F System for launching. They should be followed
exactly in step-by-step sequence for a successful flight.
Preparation and check-out steps are serially numbered and should be
performed in the indicated order, at least within each section. Section 1
(Steps 1 to 8) deals with the preparation of the leaflet containers. Section
2 (Steps 9 to 11) tells how to prepare the balloon ballast. Section 3 (Steps
12 to 29) gives directions for check-out of instruments. Section 4 (Steps
30 to 33) describes rigging and inflation. Section 5 describes the layout
of the balloon and equipment; Section 6 gives instructions for inflation of
the balloon; Section 7 deals with the handling of hydrogen, and Section 8
gives final direction for launching.
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WEIGHT SCHEDULE
Balloon Weight
20 pounds
9. 15 Kilograms
Gondola Assembly
27
12.25
Ballast for 60 hours
50
22. 65
Payload of Leaflets
88
40.00
if
Gross Weight 185 pounds 84.05 Kilograms
Free lift for weigh-off weight:
Daylight launching: 14% of the gross weight or 26 pounds
(11.6 kgs)
Night launching: 17% of the gross weight or 31 pounds
(13.6 kgs)
Balloon volume: 7, 925 cubic feet.
Theoretical altitude with gross weight of 185 pounds: 30, 000 feet (9200 m)
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LEAFLET CONTAINER PREPARATION
FILL LEAFLET CONTAINERS.
To do this, place the container
to be filled on the floor or table
in an inverted position and open
the dump door. The containers
are filled from the bottom as
shown.
FILL each of the four containers
with 22 pounds (10 kilograms) of
leaflets as shown.
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170F BALLOON
STEP 3.
OBTAIN A SHEET of paper, fold
as shown and install around leaf-
lets. This will prevent leaflets
from escaping from between the
dump door flap and container
wall when the dump door is
closed.
DUMP
DOOF
FLAP
BE SURE that paper is neatly
fitted as shown. This shows com-
pletion of the operation started
in Step 3.
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170F BALLOON
CLOSE the dump door with the
side flaps on the inside of con-
tainer as shown.
INSERT NYLON LINE through
the cutting cannon as shown.
Be sure that the color marked
on the cutting cannon is the same
as that on the top of the container.
Caution: Never connect cutting
cannon to plugs before installing.
This is not done until Step 43.
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INSERT nylon line through metal
fitting on leaflet container and tie
securely as shown.
Note: Nylon lines may be tied
before inverting containers.
INVERT ALL containers so
that the dump doors are on the
bottom as shown. The nylon
harness used to attach con-
tainers to the load bars is not
shown in this picture. (See
Step 32)
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TAKE OUT THE BLOCKS OF
white insulation from the top
of the instrument gondola
(container) so that the open-
ing into the ballast hopper is
exposed.
Caution: Before removal of
this insulation notice the po-
sition of each piece so it may
be replaced in the same pat-
tern.
The rectangular hole at the
bottom of the battery com-
partment is the opening into
the ballast hopper.
POUR 50 POUNDS OF steel
shot through screen into
ballast hopper as shown.
Caution: Do not pour steel
shot into ballast hopper with-
out screening. A funnel with
a screen in its bottom have
been provided for this pur-
pose.
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170F BALLOON
RE-INSTALL insulation over
ballast hopper and around
battery compartment as shown.
(See also Steps 26, 27 and 28. )
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CHECK-OUT AND PREPARATION OF INSTRUMENT SYSTEM CIRCUITS
STEP 12. OPEN THE DOOR WHICH covers instrument compartments. Il-
lustration shows the arrangement of both instrument compart-
ments as they may appear when first unpacked.
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STEP 13. TO PERFORM NECESSARY tasks and checks, first unfasten the
wingnut which holds the plywood base of the altitude control unit
firmly to the shelf of the upper compartment. Grasp the ply-
wood base (not the instrument) and move the unit out as shown.
The arrow points to the first contact on the contact strip. This
is designated as contact "B" in the circuit schematic, Plate I.
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170F BALLOON
STEP 14. CLEAN ALL SIX CONTACTS on altitude control system com-
mutator. Commutator strip is shown. Contacts are numbered
as shown. When cleaning, use a good grade of silver polish.
Wipe very gently parallel to the long dimension of the contacts.
Do not use too much polish so that a residue is left. Do not
touch shelves above commutator strip while cleaning contacts.
Wipe contacts clean with chamois or cloth after cleaning.
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TIMER
COMMUTATOR
STRIP
^
STEP 15. CLEAN THE FIVE CONTACTS on the timer commutator strip
shown. As for Step 14, use a good grade of silver polish. Wipe
very gently parallel to the long dimension of the contacts. Wipe
contacts clean with a chamois or cloth after cleaning.
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170F BALLOON
00
ON-0
O
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STEP 16.
USE TWO SIX-VOLT test
batteries for the circuit
checks described in the
following steps (Steps 17
to 25). Connect the colored
wire (purple) to the positive
terminal of both batteries
(terminals are marked).
Connect the white wire to
the negative terminal of
both batteries as shown.
CHECK FIRST emergency circuit.
a. Put Master Switch ON. See
Step 15.
b. With a light wire and clips con-
nect the uninsulated part of the
lower shelf to the frame of the
altitude control unit. Uninsulated
part of lower shelf, on which al-
titude control arm rests during
last half of ascent to calculated
flight pressure level, is the con-
tact for the first emergency cir-
cuit. (See Step 13) For this test
the arm should rest on the upper
insulated shelf.
c. With voltmeter provided, check
voltage across the terminals of
the motor as shown. The voltage
should read 6 volts.
d. Remove wire and clips.
TEST
VOLTAGE
(6V)
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CHECK ALTITUDE control circuit.
a. Put Master Switch ON.
b. With ballast valve at eye level, using
test wire, momentarily ground contact
B of altitude control commutator strip
(See Step 14 and Plate I) to frame of al-
titude control unit. Ballast should flow
as contact is made and stop immediately
when contact is broken. Ballast valve is
shown.
Note: Drawing shows location of ballast
valve in bottom of instrument
gondola.
CHECK STANDARD emergency circuit.
By 6V 6V 6V PLUG CONNECTORS
a. Put Master Switch ON.
b. With a light wire and clips, successively
ground contacts 1, 2, 3, 4, and A on the
Altitude Control Unit commutator strip
to the instrument frame. Check each
corresponding plug and motor contacts in
turn with the voltmeter. Voltage in each
instance should read six volts. Illustra-
tion is a partial schematic to show check
points.
Contact No. 1 activates circuit for Plug
No. 1.
Contact No. 2 activates circuit for Plug
No. 2.
Contact No. 3 activates circuit for Plug
No. 3.
Contact No. 4 activates circuit for Plug
No. 4.
Contact A activates circuit for Motor
Contact MA.
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STEP 20. CHECK THE POSITION OF the altitude control arm as shown.
This arm must be riding on the upper short shelf at launching.
If this arm touches the uninsulated part of the lower shelf when
the Master Switch is on, the motor will be activated and the
plugs will fire in sequence. Step 13 also shows the proper
launching position of the control arm.
After satisfactory check, replace and refasten the Altitude
Control Unit in the upper instrument compartment with the wing
nut as shown in Step 12.
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ALTITUDE
CONTROL
UNIT
STEP 21. CHECK TIMER control circuit. (Steps 21 - 24 inc.)
a. Remove timer disc.
b. Wind clock with key provided.
c. Replace timer disc.
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STEP 22. REPLACE TIMER DISC lock nut but do not tighten. The nut must
be loose so that the timer disc may be moved easily. Lock nut is
shown by finger.
The timer disc has a pointer attached at the zero reading. Test
the contact of the pin on the timer disc pointer with the timer
commutator strip. Make certain that the pointer makes good
contact. If the contact is not good, the pointer can be bent in or
out by hand until the correct adjustment is made.
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170F BALLOON
STEP 23. TURN TIMER DISC pointer counterclockwise until pointer contacts
No. 1 contact on the timer commutator strip. Contact No. 1 is
the first contact reached by the timer disc pointer as it travels
counterclockwise.
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30 20
PUT MASTER SWITCH ON.
Set Selector Switch on Position
1; check plugs 1, 2, 3 & 4
for 6 volts.
Set Selector Switch on Position
2; check plugs 1, 2 & 3 for
6 volts.
Set Selector Switch on Position
3; check plugs 1 & 2 for 6
volts.
Set Selector Switch on Position
4; check plug 1 for 6 volts.
Move timer disc pointer coun-
terclockwise to Contact No.
2; check plug 2 for 6 volts.
Move timer disc pointer to
Contact No. 3; check plug
3 for 6 volts.
Move timer disc pointer to
Contact No. 4; check plug
4 for 6 volts.
40
2
TO NUMBERED PLUGS
3 ( ,Q2
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STEP 25.
SET THE LEAFLET drop
timer. Select the required
flight duration hour num-
ber plus an estimated time
required for rigging and
inflation.
Place this number opposite
the white index mark (shown
in Step 23) on the timer com-
mutator strip. Tighten lock
nut.
Set drop circuit Selector
Switch in accordance with
table.
Selector
Switch
Live
Position
Plug
1
1-2-3-4
2
1-2-3
3
(#4 fires approx.
60 min. later)
1-2
INSTALL THE TWO 6-volt
batteries in the flat position
as shown.
Connect the colored wire to
the positive terminals of
both batteries.
Connect the white wire to
the negative terminals of
both batteries.
Make sure that the bat-
teries are placed so that
the terminals are at oppo-
site ends of the battery
compartment as shown.
This will prevent short
circuits caused by the
touching of battery ter-
minals.
(#3 fires approx.
40 min. later;
#4 fires approx.
60 min. later )
(#2 fires approx.
20 min. later;
#3 fires approx.
40 min. later;
#4 fires approx.
60 min later)
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STEP 27. TWO SMALL WATER cans are provided. Fill these cans with
water to the black line marked on each. Screw the caps on
securely.
Place the cans of water over the batteries as shown.
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INSTALL top piece of insu-
lation over the batteries and
water cans as shown.
INSTALL plywood hanger
sheet in place, close flaps
and install washers and wing
nuts as shown.
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RIGGING, INFLATION AND CAP INSTALLATION
AT THE LAUNCHING site,
concurrent with balloon
layout:
Check the position of the
altitude control arm (Step
13). This arm must be
riding on the upper, short
insulated shelf at launch.
Re-check setting of the
leaflet drop timer. (Step
15).
Pull pin to start timer.
Note time allowed for
launch.
TURN MASTER SWITCH
ON. (Step 15)
Close instrument compart-
ment door.
Insert instrument gondola
in white insulated box as
shown.
Install the two top insula-
tion pieces as shown. The
five circuit wires will pro-
trude from one side between
the two pieces of insulation.
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STEP 32. ATTACH LOAD BAR ASSEMBLY as shown. The nylon support
line for the insulated box goes from one side to the other side
of the box through the ring of the snap at the upper part of the
load bar assembly. (Note: Insulating blocks have been removed
for this photograph. )
Attach the leaflet containers to the outer points of the load bars
as shown, matching the corresponding color codes of the con-
tainer and the load bar marking.
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STEP 33. TAPE THE LEAFLET containers and the insulated box together
in the positions shown.
Connect the top hooks of the load bar assembly to the balloon
suspension.
Attach appropriate free-lift weight.
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LAYOUT OF BALLOON AND EQUIPMENT
UPON ARRIVAL AT the launching site, the ground cloth should be laid out
in the down-wind direction. The gondola, loaded with ballast, leaflets and
free-lift weight makes an excellent anchor and should be placed on the up-
wind end of the ground cloth.
PLACE THE BOX containing the balloon adjacent to the ground cloth at the
up-wind end. Open the top of the box and split it down the sides to make it
lie flat.
PICK THE BALLOON up gently and place it on the ground cloth. The bal-
loon is now in position to be rolled out to its full length.
ROLL OUT THE balloon. Two men, one on either side, should do this. In
handling the balloon, get underneath to lift it. Do not pull or, grip the ma-
terial with the fingers. Light-weight, metal-free gloves should be worn to
prevent the fingernails from damaging the fragile balloon material. Every
precaution must be taken in handling the balloon to insure that no damage
will occur that could result in a leaky balloon. During this operation a
third person should place the harness and accessories in such a position
that he can secure the gondola to the harness. Make sure that no twists
occur in the suspension lines and gondola load bars.
THE DIFFUSER CAN now be inserted into the inflation tube making sure
that no twists are evident in the tubing. The inflation tubing should be
taped tightly to the diffuser to prevent gas leakage.
BEFORE BEGINNING to inflate the balloon, the open appendix at the base
of the balloon should be temporarily tied shut, being careful not to damage
the skirt material in the process.
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Section 6.
INFLATION REQUIRES A man to support the apex of the balloon until it
is supported by the gas. This same man will regulate the reefing sleeve
after there is enough gas in the balloon so that it is erect and can sup-
port itself. The reefing sleeve serves to protect the balloon and holds
all the slack material of the balloon together on inflation, preventing the
wind from making a big uncontrollable sail of it. Judgement should be
used to prevent this and yet allow room for the gas to expand freely.
ANOTHER MAN IS NEEDED TO regulate the flow of gas into the balloon
through the duct inflation tube. Gas flow can be fairly rapid; however,
violent fluttering of the tubing should be avoided. This man can also
steer the inflation bubble to offset the effect of the wind, by keeping ten-
sion on the duct. Once the balloon is vertical, gas flow can be increased
to maximum without ripping or violent flutter occurring in the inflation
tube. During inflation, last minute checks on the rigging and equipment
can be accomplished. With 14 German 6 cubic meter bottles turned on in
the manifold, continue inflation until the gondola is weighed off and the
free lift weight starts to become light. Decrease the rate of gas flow and
holding the gondola in place, carefully determine if the balloon is light
or heavy. Slowly add gas until the system is in equilibrium. After
achieving initial balance, secure a closer check by lifting system approxi-
mately three feet in the air and check for settling. Add gas as necessary
to achieve as close balance as possible. Once gas is introduced into the
balloon there is no provision for release of excess gas. Consequently,
caution is necessary to prevent over-inflation. Securely tie off inflation
duct and cut off excess material approximately 20 cm below tie off point.
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Hydrogen can be very dangerous if not handled properly. An air-hydrogen
mixture containing between 7 and 72 percent hydrogen by volume is explo-
sive, and in the higher ranges will burn vigorously. On the other hand, as
long as air is excluded from mixing with the hydrogen, and no flames,
sparks, or hot surfaces in excess of 400OF are permitted near the gas,
there is no danger.
SMOKING MUST NOT BE ALLOWED
in the area when using hydrogen. To minimize the chances of generating
static sparkE during inflation, the
HYDROGEN CYLINDER AND INFLATION NOZZLE
MUST BE ELECTRICALLY GROUNDED.
There is no danger of air being sucked into the balloon during inflation with
this type balloon with the appendix clipped, shut, or tied off. The standard
German hydrogen cylinder has an expanded volume of gas of 6 cubic meters
(211 cubic feet) and will provide (at 140 atmospheres or 2000 psi or better)
at least 6. 35 kilograms (14 pounds) of lift. A full German hydrogen cylin-
der weighs approximately 80 kilograms (176 pounds) and has left-hand
threads.
-30-
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CHECK THE VOLTAGE across the terminals of plugs 1, 2, 3 and 4
with the voltmeter provided. The voltage should be zero in each case.
After satisfactory test, remove the short from each cannon socket in
turn and attach each plug to its respective cannon socket on a leaflet
container, matching the color coding marked on plug and socket.
Mating of the plugs and sockets is shown in Step 32.
Await D-hour set on timer for launch.
Launch by cutting off free-lift weight.
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Balloon Delivery System
J-9-10-300
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Page
GENERAL DESCRIPTION 1
Capability 2
PERFORMANCE CHARACTERISTICS 3
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J-9-10-300 BALLOON
Abstract - This balloon is a larger version of the J-100 balloon, and
being larger it is able to carry greater loads to higher altitudes. This
means that longer drift distances can be obtained using the J-9-10-300
than could be possible with the J-100. In general the J-9-10-300 has a
capability of 250 to 400 miles distance, but the higher burst altitudes
may complicate the problem of predicting flight and leaflet impact.
In this section the performance characteristics of the J-9-10-
300 balloon are presented, with tables showing the rate of rise, and
time spent within 5000-foot increments of altitude.
General Description - The J-9-10-300 is the big brother of the J-100.
It has a nominal weight of 300 grams as compared with 100 grams for
the J-100. The J-9-10-300 is used meteorologically as a load carry-
ing balloon for the radiosonde. Being a larger balloon it is able to
carry greater loads to higher altitudes. Two different payloads were
tested for this study, a 5 and a 10 pound load. The burst altitudes re-
sulting were 58, 000 feet and 46, 000 feet, respectively. It is readily
apparent then that longer drift distances can be obtained using the
J-9-10-300 than could be with the J-100. The higher burst altitudes
may, however, complicate the prediction problem as winds at these
higher altitudes are not as commonly reported as those for the lower
altitudes .
If long drift distances are the objective, they are most easily
obtained by selecting a leaflet with a slow rate of descent and releasing
it at very high altitudes1. An example of such a leaflet is the autorota-
ting leaflet with a ground rate of descent (Vo) of 1.3 feet/second. The
time down of this leaflet from 58, 000 feet is about 7. 5 hours and from
46, 000 feet, 6. 7 hours. Using the slowest rate of rise reported here
(300 grams free lift), the time to burst is 1. 9 hours for the 58, 000 foot
burst and 1. 5 hours for the 46, 000 foot burst. These times are sum-
marized on the following page.
1
This does not follow where there is a reversal of winds at the higher
altitudes, causing the leaflets to drift first one way and then the oppo-
site way.
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J-300 BALLOON
Load Balloon time Leaflet time to Total time
(pounds) to burst (hours) impact (hours) (hours)
5 1.9 7.5 9.4
10 1. 5 6.7 8.2
Assuming an average 40 mph' wind, these total air times of 9. 4 and
8. 2 hours from balloon launch to leaflet impact yield total drifts of 376
and 328 miles, respectively2.
In general, then, the J-9-10-300 can be thought of as having a
250 to 400 mile capability, although it may be preferable to use the Pil-
low balloon for these distances, especially when winds at the very high
altitudes are lacking.
1
40 mph = 35 knots, an average wind condition at altitude.
2 The distances are obtained by multiplying the total air time by the
average wind, e. g., 9. 4 hours x 40 mph = 376 miles.
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J-300 BALLOON
PERFORMANCE CHARACTERISTICS OF THE J-9-10-300
As mentioned under the section "General Description" this bal-
loon is basically the J-100 in a larger size. The J-9-10-300 performs
similarly to the J-100; the only important differences being the larger
payloads carried and higher burst altitudes attained.
The problem solving techniques described for the J-100 are the
same as those to be used for the J-9-10-300. It might be repeated that
forecasts of the winds at higher altitudes are necessary to use this bal-
loon system to best advantage, and that special arrangements may have
to be made with the weather services to obtain the necessary informa-
tion.
The performance characteristics of the J-9-10-300, with 5 and
10-pound payloads, are presented in the following tables.
Table 1 - provides the rate of rise of the balloon within each
5000-foot increment of altitude from 0 to 60, 000 feet.
Table 2 - shows the time spent by the balloon between each 5000-
foot increment of altitude from 0 to 60, 000 feet.
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Table 1. J-9-10-300 Performance Characteristics
Incremental Rates of Rise
DAYTIME FLIGHTS
Rate of Time to
Free Lift Burst Rise Burst Incremental
(grams) Alt. (ft) (ft/min) (min) 0-5 5-10 10-15 15-20
300 58,000 520 112 540 510 480 480
1,000 58,000 820 71 1000 950 900 850
10 Pound Load
300 46, 000 510 91 650 600 500 460
700 46, 000 690 67 1000 1000 850 650
1,000 46,000 880 52 1100 1100 1100 1000
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Table 1. J-9-10-300 Performance Characteristics
Incremental Rates of Rise
DAYTIME FLIGHTS
Rate of Rise (ft/min)
20-25 25-30 30-35 35-40 40-45 45-50 50-55 55-60
5 Pound Load
480
480
490
500
520
550
590
630
800
750
800
800
800
800
800
850
450
450
480
500
500
510
600
600
600
600
650
650
900
800
700
700
700
700
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Table Z. J-9-10-300 Performance Characteristics
Incremental Time Factors
DAYTIME FLIGHTS
Rate of Time to
Free Lift Burst Rise Burst Time Spent
(grams) Alt. (ft) (ft/min) (hours) 0-5 5-10 10-15 15-20
300 58,000 520 1.87 0.15 0.16 0.17 0.17
1,000 58,000 820 1.19 0.08 0.09 0.09 0.10
300 46,000 510 1.52 0.13 0.14 0.17 0.18
700 46,000 690 1.11 0.08 0.08 0.10 0.13
1,000 46,000 880 0.87 0.07 0.07 0.07 0.08
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Table Z. J-9-10-300 Performance Characteristics
Incremental Time Factors
DAYTIME FLIGHTS
Between Altitude Levels (hours)
20-25
25-30
30-35
35-40
40-45
45-50
50-55
55-60
0.17
0.17
0.17
0.17
0.16
0.15
0.14
0.09
0.11
0.11
0.11
0.11
0.11
0.11
0.11
0.06
0.18
0.18
0.17
0.17
0.17
0.03
0.14
0.14
0.14
0.14
0.13
0.03
0.09
0.11
0.12
0.12
0.12
0.02
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