FEASIBILITY INVESTIGATION OF INFLATABLE STRUCTURE FOR HIGH ALTITUDE AIRCRAFT CONTRACT AF 33(600) - 36179

• Document Type: FOIA
• Collection: FOIA Collection
• Document Number (FOIA) /ESDN (CREST): 02014934
• Release Decision: RIFPUB
• Original Classification: U
• Document Page Count: 135
• Document Creation Date: March 8, 2023
• Document Release Date: April 15, 2019
• Case Number: F-2016-01486
• Publication Date: December 20, 1957

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�Nlior C-- eg- 3 /
arkpLi 3c)t 5-
GOODINEAR
GOODYEAR AIRCRAFT CORPORATION
AKRON, OHIO
THIS DOCUMENT CONTAINS INFORMATION AFFECTING THE NATIONAL DEFENSE OF
THE UNITED STATES WITHIN THE MEANING OF THE ESPIONAGE LAWS, TITLE 18,
U.S.C., SECTIONS 793 AND 794. THE TRANSMISSION OR THE REVELATION OF ITS
CONTENTS IN ANY MANNER TO AN UNAUTHORIZED PERSON IS PROHIBITED BY LAW.
FEASIBILITY INVESTIGATION
OF INFLATABLE STRUCTURE
FOR HIGH- ALTITUDE AIRCRAFT
CONTRACT AF 33(600)- � 36179
GE'R 8499 December 20, 1957
Copy No. 3
COPYRIGHT 1957
GOODYEAR AIRCRAFT CORPORATION SEE/PET
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TABLE OF OONTENTS
Page
Summary
15
Introduction
16
Determination of Specimens
18
Determination of Similitude Factors For Test Panels
20
Determination of Aerodynamic Loads
28
Test Procedure
50
Test Results
53
Conslusions and Recommendations
.56
Appendix A, Test Results in Tabular Form
584
Appendix B, Test Results in Graphical Form
99
Appendix C, Photographs of Tests
121
References
135
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Figure No.
LIST OF ILLUSTRATIONS
Title
Page
1
Planforms of Test Panel and Simulated Wing
19
(Aspect Ratio = 8.15)
2
Planforms of Test Panel and Simulated Wing
19
(Aspect Ratio = 3.70)
3
Planform of Typical Tapered Wing
21
4
Relationship of Test Panel with Respect to
26
Simulated Wing (Aspect Ratio = 3.7)
5
Relationship of Test Panel with Respect to
26
Simulated Wing (Aspect Ratio = 8.15)
6
Design Gust Velocity, Altitude vs. Ude
33
7
L/D vs 04i, M = .80, Altitude 80,000
34
8
LID bs C, M = .80, Altitude 80,000
35
9
Total Gust Load vs Altitude (Aspect Ratio =
36
8.15)
10
Total Gust Load vs Altitude (Aspect Ratio =
37
3.70)
11
load Coefficient vs Semispan (Aspect Ratio =
38
8.15)
12
Load Coefficient vs Semispan (Aspect Ratio =
39
3.70)
13
Load vs Semispan AR = 8.15
40
14
Load vs Semispan AR = 3.70
41
15
Load Distribution vs Semispan AR = 8.15
42
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LIST OF ILLUSTRATIONS
Figure No. Title Page
16 Load Distribution vs Semispan AR = 3.70 43
17 Scale Locations (Aspect Ratio = 8.15) 52
18 Scale Locations (Aspect Ratio = 3.70) 52
19 Cross-Section of Test Panel, Contour Stability 54
Check
20 AR = 3.70, Deflections for 20%, 40%, 60% of 100
Maximum Symmetrical Load at 20 PSI Internal
Pressure, Cover Ply Material - Dacron
21 AR = 3.70, Deflections for 20%, 40%, 60% of 101
Maximum Symmetrical Load at 40 PSI Internal
Pressure, Cover Ply Material - Dacron
22 AR = 3.70, Deflections for 80% & 100% of Maximum 102
Symmetrical Load at 40 PSI Internal Pressure,
Cover Ply Material - Dacron
23 AR = 3.70, Deflections for 20%, 40% & 60% of 103
Maximum Symmetrical Load at 60 PSI Internal
Pressure, Cover Ply Material - Fortisan
24 AR = 3.70, Deflections for 80% & 100% of Maximum 104
Symmetrical Load at 60 PSI Internal Pressure, Cover
Ply Material - Fortisan
25 AR = 3.70 Deflections for 20% & 40% of Maximum 105
Unsymmetrical Load at 60 PSI Internal Pressure,
Cover Ply Material - Fortisan
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Figure No.
26
27
28
29
30
31
32
33
71-
LIST OF ILLUSTRATIONS
Title
AR = 3.70 Deflections for 60%, 80% & 100% of
Maximum Unsymmetrical Load at 60 PSI Internal
Pressure, Cover Ply Material - Fortisan
AR = 8.15, Deflections for 15% of Maximum
Symmetrical Load at 40 PSI Internal Pressure,
Cover Ply Material - Fortisan
AR = 8.15, Deflections for 15% of Maximum
Symmetrical Load at 60 PSI Internal Pressure,
Cover Ply Material - Fortisan
AR = 8.15, Deflections for 20% & 40% of Maximum
Unsymmetrical Load at 40 PSI Internal Pressure,
Cover Ply Material - Fortisan
AR = 8.15, Deflections for 20% & 40% of Maximum
Unsymmetrical Load at 60 PSI Internal Pressure,
Cover Ply Material - Fortisan
AR = 8.15, Deflections for 15% & 30% of Maximum
Symmetrical Load at 20 PSI Internal Pressure,
Cover Ply Material - Dacron with Fiberglas
AR = 8.15, Deflections for 45% & 60% of Maximum
Symmetrical Load at 20 PSI Internal Pressure,
Cover Ply Material - Dacron with Fiberglas
AR = 8.15, Deflections for 40%, 80%, & 100% of
Maximum Unsymmetrical Load at 20 PSI Internal
Pressure, Cover Ply Material - Dacron with
Fiberglas
Page
106
107
108
109
no
111
112
113
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Figure No.
34
35
36
37
38
39
40
LIST OF ILLUSTRATIONS
Title Page
AR - 3.70, Average Deflection for 100% of 114
Maximum Symmetrical Load
AR = 8.15, Aver4ge Deflection for 15% of 115
Maximum Symmetrical Load
AR = 8.15, Average Deflection for 40% of 116
Maximum Unsymmetrical Load
AR = 3.70, Comparison of Twist and Deflection 117
of Test Panel with Simulated Wing for 100% of
Symmetrical Load at 20 PSI Internal Pressure,
Cover Ply Material - Fortisan
AR = 3.70, Comparison of Twist and Deflection of 123
Test Panel with Simulated Wing for 100% of
Unsymmetrical Load at 60 PSI Internal Pressure,
Cover Ply Material - Fortisan:
AR = 8.15, Comparison of Twist and Deflection of 119
Test Panel with Simulated Wing for 60% of Symmetrical
Load at 20 PSI Internal Pressure, Cover Ply
Material - Dacron with Fiberglas
AR = 8.15 Comparison of Twist and Deflection of Test 120
Panel with Simulated Wing for 100% of Unsymmetrical
Load at 20 PSI Internal Pressure, Cover Ply Material -
Dacron with Fiberglas
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LIST OF TABLE'S
Table No. Title Page
1 Symmetrical Load Schedule, AR = 3.70 44
2 Symmetrical Load Schedule, AR = 8.15 45
3 Unsymmetrical Load Schedule, AR = 3.70 47
4 Unsymmetrical Load Schedule, AR = 8.15 48
5 Contour Change of Fortis an Specimen 55
at 40 PSI Internal Pressure
6 Warp Readings, AR = 8.15 62
7 Warp Readings, AR = 3.70 63
8 AR = 3.70, 20% of Maximum Symmetrical Load 64
at 20 PSI Internal Pressure, Cover Ply
Material - Dacron
9 AR = 3.70, 40% of Maximum Symmetrical Load 65
at 20 PSI Internal Pressure, Cover Ply
Material - Dacron
10 AR = 3.70, 60% of Maximum Symmetrical Load at 66
20 PSI Internal Pressure, Cover Ply
Material - Dacron
11 AP = 3.70, 40% of Maximum Symmetrical Load 67
at 40 PSI Internal Pressure, Cover Ply
Material Dacron
12 AR = 3.70, 60% of Maximum Symmetrical Load
at 40 PSI Internal Pressure, Cover Ply
Material - Dacron
68
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Table No.
UST OF TABLES
Title Page
13 AR = 3.70, 80% of Maximum Symmetrical Load 69
at 40 PSI Internal Pressure, Cover Ply
Material - Dacron
14 AR = 3.70, 100% of Maximum Symmetrical Load 70
at 40 PSI Internal Pressure, Cover Ply
Material - Dacron
15 AR = 3.70, 20% of Maximum Symmetrical Load 71
at 60 PSI Internal Pressure, Cover Ply
Material - Fortisan
16 AR = 3.70, 40% of Maximum Symmetrical Load
at 60 PSI Internal Pressure, Cover Ply
Material - Fortisan
17 AR = 3.70, 60% cf Maximum Symmetrical Load
at 60 PSI Internal Pressure, Cover Ply
Material - Fortisan
18 AR = 3.70, 80% of Maximum Symmetrical Load 74
at 60 PSI Internal Pressure, Cover Ply
Material - Fortisan
AR = 3.70, 100% of Maximum Symmetrical Load 75
at 60 PSI Internal Pressure, Cover Ply
Material - Fortisan
20 AR = 3.70, 20% of Unsymmetrical Load at 60 76
PSI Internal Pressure, Cover Ply Material -
Fortisan
72
73
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Table No.
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LIST OF TABLES
Title
21 AR = 3.70, 40% of Unsymmetrical Load at 60 77
PSI Internal Pressure, Cover Ply Material -
Fortisan
22 AR = 3.70, 60% of Unsymmetrical Load at 78
60 PSI Internal Pressure - Cover Ply
Material - Fortisan
23 AR = 3.70, 80% of Unsymmetrical Load at 79
60 PSI Internal Pressure, Cover Ply
Material - Fortisan
24 AR = 3.70, 100% of Unsymmetrical Load at 80
60 PSI Internal Pressure, Cover Ply
Material - Fortisan
25 AR = 8.15, 15% of Maximum Symmetrical Load 81
at 40 PSI Internal Pressurb, Cover Ply
Material - Fortisan
26 AR. = 8.15, 15% of Maximum Symmetrical Load 82
at 60 PSI Internal Pressure, Cover Ply
Material - Fortisan
27 AR = 8.15, 20% of Unsymmetrical Load at
40 PSI Internal Pressure, Cover Ply
Material - Fortisan
28 AR = 8.15, 40% of Unsymmetrical Load at 40
PSI Internal Pressure, Cover Ply Material -
Fortisat
GOOD/'EAR
AIRCRAFT
GER il+99
Page
83
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Table No.
29
30
31
32
33
34
3.5
36
LIST OF TABLES
Title
AR = 8.15, 20% of Unsymmetrical Load at
60 PSI Internal Pressure, Cover Ply
Material - Fortisan
AR = 8.15, 40% of Unsymmetrical Load at
60 PSI Internal Pressure, Cover Ply
Material - Fortisan
AR = 8.15, 15% of Maximum Symmetrical Load
at 20 PSI Internal Pressure, Cover Ply
Material - Dacron with Fiberglas
AR = 8.15, 30% of Maximum Symmetrical Load
at 20 PSI Internal Pressure, Cover Ply
Material - Dacron with Fiberglas
AR = 8.15, 45% cf Maximum Symmetrical Load
at 20 PSI Internal Pressure, Cover Ply
Material - Dacron with Fiberglas
AR = 8.15, 60% of Maximum Symmetrical Load
at 20 PSI Internal Pressure, Cover Ply
Material - Dacron with Fiberglas
AR = 8.15, 40% of Unsymmetrical Load at
20 PSI Internal Pressure, Cover Ply Material
Dacron with Fiberglas
AR = 8.15, 80% of Unsymmetrical Load at 20
PSI Internal Pressure - Cover Ply Mateiral -
Dacron with Fiberglas
Page
8.5
87-
88
89
90
92
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Table No.
LIST OF TABLES
Title
37 AR = 8.15, 100% of Unsymmetrical Load at 93
20 PSI Internal Pressure, .Cover Ply Material -
Dacron with Fiberglas
38 AR = 3.70, 100% of Unsymmetrical Load at 95
60 PSI Internal Pressure, Cover Ply Material -
Fortisan
39 AR = 3.70, 100% of Maximum Symmetrical Load at 96
60 PSI Internal Pressure, Cover Ply Material -
Fortisan
40 AR = 8.15, 60% of Maximum Symmetrical Load at 97
20 PSI Internal Pressure, Cover Ply Material -
Dacron with Fiberglas
41 AR = 8.15, 100% of Unsymmetrical Load at
20 PSI Internal Pressure, Cover Ply Material -
Dacron with Fiberglas
Page
98
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Photograph
1
2
3
4
5
6
LIST OF PHOTOGRAPHS
Title
Zero Reading Position, AR = 3.70, 100% of
Maximum Symmetrical Load at 40 PSI Internal
Pressure, Cover Ply Material - Dacron
Deflected Reading Position, AR = 3.70, 100%
of Maximum Symmetrical Load at 40 PSI
Internal Pressure, Cover Ply Material -
Dacron
Deflected Reading Position, AR = 3.70, 100%
of Maximum Symmetrical Load at 40 PSI
Internal Pressure, Cover Ply Material -
Dacron
Zero Reading Position, AR = 8.15, 15% of
Maximum Symmetrical Load at 40 PSI Internal
Pressure, Cover Ply Material - Fortisan
Deflected Reading Position, AR = 8.15,
15% of Maximum Symmetrical Load at 40 PSI
Internal Pressure, Cover Ply Material -
Fortisan
Deflected Reading Position, AR = 8.15,
15% of Maximum Symmetrical Load at 40 PSI
Internal Pressure, Cover Ply Material -
Fortisan
Page
122
123
124
125
126
127
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Photograph
7
8
9
10
11
12
LIST OF PHOTOGRAPHS
Title
Deflected Reading Position, AR = 8.15, 20%
of Maximum Unsymmetrical Load at 40 PSI
Internal Pressure, Cover Ply Material -
Fortisan
Deflected Reading Position, AR = 8.15, 20%
of 20% of Maximum Unsymmetrical Load at
40 PSI Internal Pressure - Cover Ply
Material - Fortisan
Zero Reading Position, AR = 8.15, 45%
of Maximum Symmetrical Load at 20 PSI
Internal Pressure, Cover Ply Material -
Dacron and Fiberglas
Deflected Reading Position, AR = 8.15,
45% of Maximum Symmetrir.J11 Load at 20
PSI Internal Pressure - Cover Ply Material -
Dacron with Fiberglas
Deflected Reading Position, AR = 8.15,
45% of Maximum S5qumetrical Load at 20 PSI
Internal Pressure, Cover Ply Material -
Dacron with Fiberglas
Deflected Reading Position, AR = 8.15, 100%
of Maximum Unsymmetrical Load at 20 PSI
Internal Pressure, Cover Ply Material -
Dacron with Fiberglas
Page
128
129
130
133.
132
133
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Photograph
13
LIST OF PHOTOGRAPHS
Title
Deflected Reading Position, AR = 8.15, 100%
of Maximum Unsymmetrical Load at 20 PSI
Internal Pressure, Cover Ply Material - Dacron
with Fiberglas
Page
134
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SUMMARY
The ptrpose of this brief investigation was to demonstrate the feasibility
of using airmat material for the construction of an aircraft which could
operate at an altitude of 80,000 feet and a speed of Mach .8. In order to
expedite this program, the test specimens used were made from available
materials and merely simulated wing constructions.
Combinations of nylon, Dacron, Fortisam, and fiberglas in the form
of test panels simulating wings with aspect ratios of 3.7 and 8.15 show
that a considerable amount of leeway is available to the aeronautical
engineer in choosing the construction desired. For the wing loadings of an
aircraft performing a typical reconnaissance mission, it has been shown that
airmat material can be provided which will supply the structural integrity
required.
The next step would be to define a specific mission and make a parametric
study of the variables concerned to enable the design of an optimum air-
craft, which still retains the radar transparency capabilities and light
weight properties of airmat construction.
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INTRODUCTION
The aircraft designed to perform a high altitude reconnaisance mission
should, among other items, have the capability of escaping radar detection
in so far as practical. This requirement suggests as airfram4 materials
airmat and fiberglas, both of which have relatively low radar reflectivity
qualities.
As an airframe material airmat has been successfully used in Goodyear
Aircraft's "Inflatoplane". This vehicle is a light weight, low speed aircraft
with considerably less demanding aerodynamic and structural requirements
than an aircraft capable of performing a high altitude reconnaisance mission.
To offset this difference in requirements, an airmat designed to operate
at internal pressures up to eight times gre0.ter than the airmat previously
used has been proposed.
The initial buckling strength of airmat structure being primarily
dependent upon the internal pressure, the proposed increase should satisfy
the strength requirements. In order to satisfy the stiffness or deflection
requirements, three approaches have been suggested, each having desirable
features. The first approach employs airmat with neoprene coated Dacron
cover plys which make it readily foldable when deflated yet increases the
stiffness over the nylon al,rmat used in the Inflatoplane. The second
approach employing Fortisan in place of Dacron is an improvement on the
first with respect to stiffness because Fortisan has a grater modulus of
elasticity. However, in this case the folding life will be reduced because
the Fortisan fibers tend to brpak down under repeated foldings. The third
approach employing fiberglas as cover ply material eliminates the folding
feature but greatly increases the stiffness.
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As substantiating evidence of the contractors belief that airmat in
some form could feaseably be used as airframe material for an aircraft capable
of performing a high altitude reconnaisance mission, a test program was
requested by the Air Force.
Normally the first phase of a complete test program of this nature
would be the determination of the optimum wing configuration. The second
phase would then be the actual testing of test panels simulating this config-
uration, and the third phase would be the correlation and presentation of
the results of the first two phases.
Due to the short time duration of this program, 15 October 1957 to 15
December 1957, the logical sequence of procedure noted above could not be
folaoweu. Instead it was necessary to make some basic assumptions concern-
ing the wing configuration so that a test program could be initiated immediately.
.As a result, the panels tested do not represent optimum wing configurations.
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DETERMINATION OF SPECIMENS
In order to satisfy the time requirements, it was necessary to use
materials which were readily available from Goodyear Tire and Rubber
Company. Considering the advantage of a wide range of internal pressure
capability, high pressure airmat was selected. This selection limited the
specimen shapes to flat panels three inches thick with a maximum width of
forty inches. This width limitation, in conjunction with the parametric
requirements of an aspect ratio equal to nine and a maximum thickness ratio
of ten per cent or leas, prevented the choice of a very large sweep back
angle. Based primarily upon the above noted limitations, two each of the
test panels shown in Figures 1 and 2 were ordered from Goodyear Tire and
Rubber Company.
All of these test panels have nylon as the basic airmat material.
One each of the two configurations were ordered with three cover plys
of Dacron, and the remainder with three cover plys of Fortisan. The top
cover ply direction was along the length of the panel and the warp directions
of the other two plys were on alternating forty-five degree biases.
It should be noted that the actual aspect ratios of the two specimens
are 5.24 and 11.5. However, as described later, the corresponding aspect
ratios for the wings simulated by these test panels were determined as 3.7
and 8.15 respectively.
Since an aircraft utili4ng airmat construction would probably have
a through wing, the test panels were constructed to simulate the full span
and thus more closely approximate the wing support conditions.
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�����
10,55�
Section A-A (Expanded and Rotated)
135.0"
rter Cho d Line
Outline of Test Panel
(SIN � ) ----- Outline of Simulated WI
40.0n
Planforms of Test Panel and Sim,1
(Aspic t Ratio = 8.15)
Figure 1
Section B-B (Expanded and Rotat,3d)
Outline of Test Panel
-.�
Quarter Chord Line
61.0"
Outline of Simulated. Wing
5-81i
Planforms of Test Panel
and Simulated Wing (Aspect Ratio 3 *7)
Figure 2
---
:ell .58"
�7.0n
23.9"
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DETERMINATION OF SIKELITMIE FACT.QAP..F.QR ,PANE:Ls
Considering that the present state of the art for weaving of airmat
limits the airfoil shapes to those which are symmetrical, an NACA 66-010
airfoil was selected as one which conCeivably could be used in meeting the
aerodynamic requirements. Based upon a chord length equal to "C" and only
the forward eighty per cent of the airfoil structurally effective, the
following values for the structural properties of the NAGA 66-010 airfoil
were calculated.
I = .00273G3 = moment of inertia
= .0546C2 = section modulus
A = .0643C2
= enclosed cross-sectional area
and N = 1.68G = length of perimeter of enclosed cross-sectional area
For the airmat test panels, which have a rectangular cross-sectional
shape with a constant thickness of three inches, the section properties
may be expressed in terms of the width, "b" as
I = 4.5b - 2.9 = moment of inertia
= 3b - 1.93 = section modulus
A = 3b 1.93 = enclosed cross-sectional area
and N = 2b - 3.43 = length of perimeter of enclosed cross-sectional area
Equating the two values for moment of inertia results in
I = .00273G3 = 4.5b - 2.9 and
C = 1650b - 1060
Performing a similar operation on the other section properties gives
C =\/55b - 35.3 for equivalent section modulii
C =V46.7b - 30 for equivalent enclosed cross-sectional areas
and C = 1.19b - 2.04 for equivalent perimeter lengths.
20
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Obviously, all these equations relating "C" and "b" cannot be satisfied
with the same values for the variables. Thus it was necessary to compromise
in the selection of these values and then determine comparison factors
between the test specimen deflections and the wing deflections
To facilitate this comparison, theoretical deflection curves for both
the test specimen and the wing will be determined. Neglecting for now, any
torsional effects and assuming a uniform load,"w", in pounds per foot of
span length on a test specimen of the planform shape shown in Figure 3,
the moment at station "y" is�
My = 1. - y)2
(SIM)
Planform of Typical
Tapered Wing
Figure 7;
The value of "by" may be expressed as
b = bR [bR bTi y
Substitution of this value into the equation for moment of inertia gives
Iy = 4051OR ... 209 405 ibR y
, .
The deflection at station "x" equals t1,3 moment of the a diagram about
that is
4 x
x
L - 42.0c -
-
0 (4.h - 2.9 - 4.5 [bR bT
L Y)
= w (L, - 21,xy + xy2 _ L2y + 2L
(4.5bR - 2.9 - 4.5 Y)
0
or
3) d
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2
Let C1 = L x
C2 = -(2Lx + L2)
C3 = 2L + x
C4 = 4.5bR - 2.9
and C5 = -4.5N bJ
Using these constants, the deflection equation may be rewritten as
= E/ (c1 C2y + C3y2 _ y3) dy
0 (C4 C53)
Integratechthe result is.
jax = gE. ([ Log eL4. / { _21
C4
C2C4 5242
+ c53
5
C5
223C4
+C x IEZ c5 G
5 . 2 - 053 _ + C c54 2 4 5x 4" '52 2 'lc E334- 3G 5 5
The wing to be simulated has the same general planform and loading
except that "bR" and "bT" become "CR" and "CT" respectively. Thus
Cy = CR -ICR CTJ
y
Substitution of this value into the equation for moment of inertia results in.
1y= .00273 (CR - [CR
Letting C1 = L2x
C2 = -(2Lx +
C3
. 2L + x
K1 = .1395CR
and K2 = CT1
the deflection at "x" may be expressed as
(C1 + C y 37.2 - Y3) dY
a 3
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Integration of this equation gives
+. K21
CI c2 3C3 ,
9K1
4fSx =
[Log (1.Cl.
[22
+;]
K23 2
--7�-� 1- _
2K1 K2 2K22 K1 2K2
2K24
Ki 6K, 2
1
Ca. ,C2K1 C3K12 3K13
+
4
K2 K2
+ 1:2; 1
�
2K2 2K2 2K2.1 2K24'
1
x
[C1 K2;12
K2(Ki + K )0)
Division of the deflection equation for the wing by the deflection equation
for the test panel and evaluation of the answer results in the comparison
curves shown in Figures 4 and 5.
To compare the torsional stiffness of the test specimens with the wings
which they are simulating requires a study of both the loading and geometric
Si.
All of the loads as applied during the test were with respect to the
quarter chord line, this and the span length being the only parts of the
geometry exactly the same for both the test specimen and the wing. Since
the elastic axes of the test specimen and the wing do not coincide, it will
be necessary to establish the relationship between the torque and these axes.
Let the shear load at any spanwise station "y", for both the test specimen
and the wing be denoted as "P". Then the torque at station "y" on the test
specimen is Pdy and on the wing Pey, where dy equals the moment arm from the
quarter chord line to the elastic axis of the test specimen and eY is the
same parameter for the wing. The elastic axis for the test specimen is
located at the fifty per cent chord line and for the wing at the forty per
cent chord line, thus the values for the moment arms may be expressed as
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SECRET GOODATAR
AIRCRAFT
GER 8499
= �25by = .25(bR
y)
and e = .15C = .15(CR - y)
As previously determined, the perimeter length of the enclosed cross-
sectional area for the test specimen is N = 2b - 3.43, from which
Ny = 2(bR 3.43
For the wing, this parameter was determined as N = 1.68C, which for station
It y It
becomes
N = 1.68(C [GR. -R - L Y)
Similiarly expressing the enclosed cross-sectional areas as variables, from
the values previously noted on page 20, results in
A = 3(bR - y) - 1.93 for the test specimen and
ClAy = .0643(CR y)2 for the wing.
Reference to any aircraft structural textbook will reveal the equation,
tc = 4-1�2?
- as the expression for the twist of a thin shelled struc-
f
0
ture. Substitution into this equation gives
ly) - 3.43] dY
for the test
P 1-.25(bR - [6:a y)] [(bR - [71.�R bT
=I
4Gt3 oDR - 30- _ 1.93] 2
specimen aad
43. .150R C
[11 - Jy/ [.68(CR dY
L for the wing.
x C,
0 4Gt E0643(C - I
- �2 2
R Y
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SECRET
GomffrEAR
AIRCRAFT
GER 8499
Since only the relationship between the torsional deflections for the
test specimen and the wing is desired, the shear "P" may be considered as
a constant. Also, for simplifying the solution of these torsional deflection
equations, let El = .25 N, and H1 = '15GA
E2 = -.25(1HE11) H2 = - .15(CR CT)
E3 = 2ba. - 3.43 H3 = 1.68GR
E = -2(bR-E712T) H4 = - 1.68(GR GT)
4
E5 = 3bR 1.93 H5 = .2535C-R
E6 = - 3(ba4L.T)
H6 = - .2535(CR i', CT)
Substitution of these constants and integration of the twist equations results
p (r6 3 E1E4+ E2E4E] E5 EL2E
4Gt 5E4
in = -767- -(E54- E6x)j E62 EIE4 + E2E 2E2E4E5 [I E5 + E4xi)
Log
E62 ( ' for the test panel
and -9- = rib
[H2H1 111114 + 112113 H211411
163 H5 + 116] 2H62 H63 H5
H5(H1H4 + H2H3) H2114H52 1
[ 3
1-
3H62 3146 H5 + H6x
H2114
H1114 + H2H3
1-
1111.13)
-1H
2H 2
for the wing.
576-3
411
' 5 6
3H5)H6
1
+ Hei2
c
Dividing the twist equation for the wing by the twist equation for the test
specimen and evaluating the solution results in the comparison curves shown
in Figures 4 and 5.
25
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GOODACAR
AIRCRAFT
alt 8499
240
210
180
150
120
100
90
60
I it-J-4,
Figure 4
;.Relationship of Test Panel with
Respect to Simulated Wing
Wing Aspect Ratio = 3.70
--T�
I
�
+14-
.41
11111111111-
IIIIIIIIIII ii
L III11111.111 II
111111111
-4
II-
ir
ifid
moll
numuumniimikwit Imospa
watiner
w
T.P.
l if 111101
1
] 9T.P.
20 40 60
Percent of Semi-Span
*Non-dimensional multiplication factor for converting test
panel parameters to corresponding simulated wing parameters.
80
100
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M*
150
90
60
0
20
SECRET
Figure 5
Relationship of Test Panel with
Respect to Simulated Wing
Wing Aspect Ratio = 8.15
80
GOOD/VIE=
AIRCRAFT
GER 8499
100
*Non-dimensional multiplication factor for converting test
panel parameters to corresponding simulated wing parameters.
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SECRET GOODAEAR
AIRCRAFT
GER 8499
UtTERMINATION OF AERODYNAMIC LOADS
It was necessary to define a structural design criteria so that the
airloads on the wings could be determined. The tntentional maneuver require-
ments of the aircraft are considered to be quite small since only a recon-
naisance mission was assumed. An incremental load factor over level flight
of t 1.0 should be adequate, this permits the performance of 60 degree
level flight banked turns and any other minor pitch maneuvers that may be
required such as in take-off and landing. The-wing shall also be capable
of accepting an unsymmetrical spanwise loading condition that is realixed
when full aileron is applied during level flight.
The aircraft and of course the wing, must also be capable of accepting
the airloads when gusts are encountered. It is recognized that the probability
of gust occurance during the performance of this mission is less than
conventional aircraft, therefore it is reasonable to consider a design
derived gust value of 30 ft. per sec. which changes with altitude as shown
in Figure 6.
The geometry of the aerodynamic equivalents of the test specimens are
shown in Figures 1 and 2. A parametric analysts of the aircraft utilizing
wings of the form shown in these figures yielded the following initial
cruise lift coefficients for the best L/D.
Aspect Ratio Sweep Angle Z4C CL
4
8.15 9.6 .32
3.70 22.5 .35
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SECRET
GOODATAR
AIRCRAFT
GER 8499
These best lift coefficients are based on the performance of the following
assumed mission:
.8
80,000 feet
4,000 nautical miles
It should be noted that the optimization of CL is based on the best L/D
when the initial wing loading is permitted to change rather than on the
usual parameterF
M
=
h
=
R
=
when the initial wing loading is fixed. This can be
seen in the following equations:
Rmax =
voi: )max F \p�--,75 [2._(.1)1 v
sfc E" 705.
Rmax = 2 (a)max flpi [1-0_111) I
sfc \CD `Idol
The result of this parametric study is shown in Figures 7 and 8.
The initial wing loading (nz = 1.0 flight) for each wing is as follows:
W = CIA q = 27.2 #/ft.2 ( M = .8 at 80,000 ft altitude )
Aspect Ratio WjS = #/ft.2
8.15 8.70
3.70 9.52
By the consideration of the gust criteria as defined above and level
flight not to exceed the dynamic pressure (q) of M = .8 at 80,000 ft altitude,
the load factor ( 1 nz gust) as a function of altitude are shown in
Figures 9 and 10 respectively for the aspect ratio 8.15 and 3.70 wings.
29
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SECRET GlaikrifEAR
AIRCRAFT
GER 8499
The method and equations which were used for this calculation are from
Reference 1 and are as follows:
nz = Kg Ve Ude a
498 GI
Where Kg is the alleviation factor obtained from Reference 1 which required
the calculation of the mass parameter pg ).
Pg = 2 WjS
pgUa
It will be noted that the load factor from gust considerations are in excess
of the maneuver requirements. The design load factors are as follows:
Aspect Ratio nz
8.15 2.82
3.70 2.26
The unit symmetrical spanwise loading on each wing panel was determined.
by the graphical method outlined in Reference 2. The spanwise loadings for
the wings for a lift coefficient of 1.0 are shown in Figures 11 and 12.
For the design load factor and the dynamic pressure of the flight condition,
the spanwise loading is determined as follows:
CI,C9 = nz [(CO.nz = 1.0j q Ctc
CL
Figures 13 and 14 are then the symmetrical spanwise loadings for the two
wing panels.
As noted in the above section on the structural design criteria the wing
must be capable of accepting an unsymmetrical spanwise loading when ailerons
are deflected. Some estimate of the aileron requirements however, must be made.
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GOODOVEAR
AIRCRAFT
GER 8499
The helix angle criteria Pb of .09 for the observer - light plane catagory
was assumed to be desirable for this aircraft. With an aileron spanning
the outboard 50% of the semispan and with an aileron chord ration of .2 and
with a total deflection of 30 degrees (15 degrees each side) this helix
angle can be accomplished. For both wing panels this is calculated as follows:
k 2V /effective
.8 V(1)6.6.1
.8 [ .0096 x .4 x 30] = .092
In the above equation, the factor .8 accounts for the consideration of
elasticity of the structure; the balance of the equation and the numerical
values are from Reference 3.
Another criteria of aileron design is the desire of a Pb of 10'/sec.
2
which is the value associated with bomber aircraft at a level flight speed
corresponding to .8 CL . With .CL max's of 1.2 and 1.0 for aspect ratio's
of 8.15 and 3.70 respectively, the pb's
2
Aspect Ratio
8.15
3.70
are as follows:
8.1
9.2
This is deemed satisfactory for the purpose of this estimate.
The spanwise load4g for the unsymmetrical case is determined on the
basis that the deflection of the aileron is equivalent to a basic loading
on the wing caused by a sudden twist of the wing in the aileron section.
The Shrenk method of calculation of the spanwise loading was used as
described in Reference 4. The additional loading for a load factor of 1.0
31
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SECRET GOODAEAR
AIRCRAFT
GER 8499
plus the incremental basic loading due to aileron are shown in Figures 15
and 16 for the dynamic pressure of 27.2 #ift.2 associated with flight at
M = .8 at 80,000 ft. altitude. This dynamic pressure was assumed to be
realized at low altitude where full aileron is likely to be applied.
The aerodynamic loadings shown in Figures 13, 14, 15,and 16 were simulated
by the load schedules shown in Tables 1, 2, 3, and 4. These load schedules
were developed by dividing the symmetrical portions of the aerodynamic lift
curves into load increments in the spanwise direction. Each load increment
was chosen as a multiple of five or ten pounds and its spanwise and chord-
wise location was made to coincide with the center of pressure of the
aerodynamic load it was simulating. The antisymmetrical portions of the lift
curves were simulated in the same manner as that noted above except that
the load increments were not chosen as multiples of five or ten pounds. It
should be noted that an assumed unit weight for the wing of six tenths of
a pound per square foot times the appropriate load factor was subtracted
from the aerodynamic lift curves before the load schedules were determined.
32
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GOODAFAM
AIRCRAFT
GER 8499
80
60
Alt.,
ft (xa03)
40
20
0
.1
Figure 6
Design Gust Velocity
Altitude vs. U e
,
II
dill -I 1 1111 1
ill , 11111 1 I 1
illoildimiltilloprilill
iim 1,1 III 111111111
filiolio mg u = ..5�1-ft"1/1/301 11
0 . - II
1111111111 I I 1 1111hilk III
11111 1111 111111111111111111 lili II Oil
11111 1 1
11111111111111111111111 II IIII
inollu mum1111111111L NI
miimilmillowlim m
m 1 II II
11111 11011111 111 111 I II �1
T i 111!11 111111111 IIIIIILLir
1111101101 111 Ill
- 1:i--9!7.- H
T:
INIEN
111111111100
mum=
Nose
01111un
aulloim
puppg
Whin
0
10
20
Ude ft/sec.
30
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=
= 1000 ft2
1
2
c1.4,
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3
L.
GOOD/TAR
AIRCRAFT
GER 8499
5
314-
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2
L/D
L
12
SECRET
r� 1 1
Figure 8
LiD vs CLw
M = .80
Alt. 80,000
t
-ut
.t.11 qtt
300
1000 ft2
-A- = 30�
Sid = 500 ft2
r-
GOODALEAL1
AIRCRAFT
GER 8499
I I -
1-11-1-
0
.3
SECRET
el+
.5
.6
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GOODAEACI
AIRCRAFT
GER 8499
Figure 9
tal Oust Load
Vs
Altitude
tl
HL
10.0
8.0
6.0
1 + ONhz)Gust
(Gust Loading)
2.0
0
2
t.
�
24.
Altitude, Ft, (x 104)
6
1
�
;
mu
Design Gust
Yelocity.
U = 55 ft
Li
_
de, ft
8
AR = 8.15
= 9.55�
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GOODAEAR
AIRCRAFT
GER 8499
10.0
8.0
6.0
nz
1 + nz)Gust
(Gust Loading)
440
2.0
tr.': I. t.:411447 --:-
Th
� Figure 10
--,-Total Gust Load 7
�
�
44
41-
4.4
vs
-EEt
"44 Altitude
,17 Hii-TttE
mi
s.
mE .118
IIMPAINIMM
,L
4-
liiiU.. I II
0. Imp..
tammilikiliiiiMil
RIMMIIMAINE 1 1111ifi
I11linlip.111111 HP 11 1 1111111p � II
II
1 i a Hi�� 0 de Ft Sec
HP h 1
id .
.:� . _, 1111
!!!
1.011 -4 4 .
,
I__ 1 :---1 -
I I I I
:::t-t L
up
1111 JIiI
ON
1 1 II I I
un
1111amiiiiiiiiiii i
..
, . lull 1 1 i
7 27.2 #/ft2rt
i . .., . a Design Point 1 16:17 �.t;8C II
INIMEMEME 111 i reldIM111001 Hill $1 I
IMINNIMMIN Iii iffilill 11111111111111 11 II
HIP 11111111111111MMINIMMIONI1111111101111 il
�
F.
Design Gust:
Velocity tT 1
rt
,11,11101-1:1,
rati. 3/3 55 ftis
I I INIMIMILT.t
80
111111 11111101
11.11
10.7
1
2
Altitude, Ft (x 1014)
AR a' 3.7
.A.0/4 22.35�
6
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GOOD/WAR
AIRCRAFT
GER 8499
1.2
0.8
0.4
1
-
11
t
-
Fig-ttre 11
Load Coefficient vs Seniispan
Mill
iiiii
IIKIIIIII
DII ii
imilimmirir iiiiiiir� king! 1 1
mum IN 1 offinum mu 1
NUMMI I
11111 110111111111 iningil ifilimun
11111! infolp 1 11911011
immul ii i gig dicroffil
0111111111111101�11 lidIIIIII 111111 116 1EMI
MENU ME
difiliniliiillifilNil 1100111 11111
11111111
iiiiiiNIMiliiNii I I II 1 1
i "1 1111111 II 1,11IIII,111II1111IIII1111III
1111 Nil I ll ill I I11110111 11111
mmommor i 1 CH II
11111111111 I
EMI III9 I HI i i i IIIIIMIIIIIII 1111111 111111111111111 16111111111 1:11; 11 Ill
1 III 1 EIM MI
111111111111111111 111"11""I 11111111111 11111 111 III "I I
X =
0.2
0.4 0.6
0.8
1.0
Spanwise Station W(b/2)
Y/(1)/2)
9.56�
M = 0.80
0.565
AR = 8.15
17 rt
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-1 1 il al 1-1 4j4i
W.:H1 t i HIA HI 111! H.!� [1.11 pi] 11-4
H ilo .i.if!
Ili] WI .i.'1-L.':
. ii ,1.!
Figure 12 'T
Load Coeffieidnt ve Semispan
Semispan Station ygb/2)
GOOD/EAR
AIRCRAFT
GER 8499
..d6Le
=
22.35�
AR
=
3.70
)N,
=
0.510
M
=
0.80
39
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GOOD"EALTI
AIRCRAFT
GER 8499
90
9
80
70'
60
Load 50
lb/ft
40
30
20
10
0
.1
� ',71 -
Figure 13
Load vs Semispen
AR = 8.15
I I
14
I i
LL
1 ,
111
1.
0,2 0.4 0.6
Semispan Station y/(1)/2)
Rz = 2.82 � 40,000 Pt
q = 27.2 #/ft2
0.8
1.0
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80
70
60
3
20
10
t-
, 1
, . ,;-1,
..
i 11;.....ii
Figure 14 - �
: ; 1; 1 I 1-
Load vs Semispul
,
AR = 3.70
1
44. i I I �
-H
I I'
I t
I_Li ::...c.. .1..._ .i.
L
1
1
r
,
r
7
L.
.r
IT
il
0.2 0.4 0.6
nz = 2.26
Semispan Station yl(b/2)
40,000 Ft.
q 2.72 #/Ft
0.8
GOOD"EAR
AIRCRAFT
GER 8 .99
1.0
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41
Load
lbs/ft
33
30
25
20
15
-10
r
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GOODAVEAn
AIRCRAFT
� GER 8499
Figure 3..5
Load Distri'butionif
- � vs
Semispan
AR = 8,15
T
1.
uII
II I1 F : 111111 11
111
1
111111 :
Aileron I II
iii1111111 1111 I II 11.1 11111IIIIlIII II 1111:111 II
C
II 111111 11 I 1111 1111 1111116111
II
Tj 11�
SECRET
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X = 0.65
Act = 9033t 40":
Aileron: Outer 50% Span
T.E. 20% Chord
= 0.4
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GOOD/TAR
AIRCRAFT
GER 8499
30
20
15
Load
1bs/ft
10
-10
[it
t
11 I.
11 !
1.11
A
Li
�
1,1
111
J
it
. I LILL Lid ! Li LI
I Figure 11
st Load Distribution
j vs
Semispan
AR 311 3'70
ii
III
i � IN
111 011 111 1 III "1111111111
1101011110111011 01111.11111111111111 li
Emilipuip wog 1 iimippoll
mitimmulmo moroommum
popumulquil mullmolumim
oullmilhomobium nuellidlillii
111111111110111111111111011101111111
Lim psi Nomifilli ummum m ffilup Hil Ill Loom Timms
MI1111 111111111 'IP:: 110111111111111111111111111
11111111110 10111111111 0111111111 IIII II Milli i 111111111111111
1111111111MI INN ffi 1 11 I II HIEN Il . MI 1111061111111 I 111 I 11. iii li Ili
100111111111011100 Aileron 11111111110111111111111111 MIMI 1111111011111
= 15� CL= Lommmigoim mio ismompuipumil
milimpliguimmui Hippo iffiimpommommipllum ilipippirpo
moommohmemommummum 1111119mmillitilibild1011111 1,111110111111!!
mmulliquommummoulummoomou moimmi H II IP 101111111110111
1111111111111111111111111,11111 11111111 111111111111111 11 I 1111 1111111111111
1111101111111111111111111110111 ill 1111111101111 MINE ill 1111 I II I 11111 1 II III 11111
0111111111111 0,2 IMINIIIMEMIIIIMI � �1111111111 � 8 10 110111 1 opium
001111111111111111111 Semispan Station = y
I I 11 t 1111111 1 HMI 1 p ANN
OH!' ' I NOM
J
r
. dill II .. '1I1 li
;44 _ J... :
rAd�t o Ming2 11111
Load ,CL = 0.35 2,.. nu
95 Im .27.2 # Ft::' In. I
4111114411 -ri , Yrli, : ?..0 _ MINI 1 ill
Net Load -
1110 I MINN 1111111
I 111111111,1111111111111 II 1111111110111111 Mill
1111111111111901111111111111111111111M IIIIIII
6111111111101111111101111111111110Er
mummilommo pudiumbiomm III
1 II qiii iii MiiIiiii0 i II iiiiiiiiiill 11 RI 1111
11
-t
I I-
tt!.
t
UI
I V_
X = 0.510
A a ns 22� 21
Aileron: Outer 50% Spqn
T.E. 20% Chore
= 0.4
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GOODATAR
AIRCRAFT
GER 8499
Table 1
Symmetrical Load Schedule*
Wing Aspect Ratio = 3.70
Station** 20% of Load
In Pounds
4.7
40% of Load
In Pounds
20
60% of Load 80% of Load 100% Of Load
In Pounds In Pounds In Pounds
30 40
5.2
10
13.9
40
50
14.4
20
15.4
10
23.5
20
30
40
50
25.8
10
33.2
34.3
20
30
40
36.7
10
44.5
30
40
50
46.2
5
20
54.0
5
55.0
10
16
21
56.5
5
Total Load For
50
105
160
216
271
Half Span
*All loads applied along the quarter chord line
**Measured in spanwise direction from test panel centerline in inches
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SECRET GOOD/WAR
AIRCRAFT
GER 8499
Table 2
Symmetrical Load Schedule**
Wing Aspect Ratio = 8.15
Station
Inches From
Centerline
15%*
Load
30%*
Load
45%*
Load
60%*
',bad
75%*
Load
88%*
Load
100%*
Load
2.7
10
15
20
25
30
35
6.0
10
8.1
10
15
20
25
30
35
13.5
lo
15
20
25
30
35
18.0
10
18.9
15
20
25
30
35
19.5
10
24.7
10
15
20
25
30
35
29.7
10
lo
15
20
25
30
35
35.1
lo
15
20
25
30
35
41.0
10
10
15
20
25
30
35
45.9
lo
15
20
25
30
35
51.6
15
20
25
30
53.6
10
10
35
57.5
lo
15
20
25
30
35
634
lo
15
20
25
30
35
69.0
lo
10
15
20
25
30
35
75.0
15
20
25
30
35
78.6
lo
lo
25
80.5
15
20
30
35
874
10
15
20
25
30
42.1
Continued on Following Page
*All loads in pounds.
**All loadp.applied along the quarter chord line
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Continuation Table. 2
Symmetrical Load Schedule**
Wing Aspect Ratio = 8.15
Station
Inches From
Centerline
89.3
15%*
Load
30%*
Load
10
45%*
Load
60%*
Load
75%*
Load
80%*
Load
100%*
Load
35
93.0
10
15
20
25
30
96.1
10
35
100.0
15
20
25
30
103.5
10
35
107.5
10
15
20
25
30
111.8
10
25
35
116.0
15
20
30
121.5
6
10
35
126.0
12
18
26
25
129.5
3
8
Total Load For
96
203
312
418
526
625
708
Half Span
*All loads in pounds.
**All loads applied along the quarter chord line
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Table 3
Unsymmetrical Load Schedule*
Wing Aspect Ratio = 3.70
Station** 20% of Load 40% of Load 60% of Load 80% of Load 100% of Load
In Pounds in Pounds In Pounds In Pounds In Pounds
5.0
5.5
6.6
9.0***
5
34.5R
10
69R
15
103.5R
20
138R
12.0****
-9.2L
-13.8L
-18.4L
4.6R
9.2R
13.8R
18.4R
15.5
15
20
16.7
10
20.1
5
26.2
20
28.5
lo
34.4
5
38.3
20
41.6
10
15
46.3*****
4.6L
-4.6R
9.2L
-9.2R
13.8L
-13.8R
18.4L
-18.4R
50.1
5
52.1
16
54.3
5
Total Load On
Specimen
40
90
1381
192
**
***
****
*****
25
173R
-23L
23R
25
23L
-23R
23
All loads applied along quarter chord line except as noted
Measured in spanwise direction from test panel centerline in inches
Station at outside edge of center support. Load at this station
applied by restraining vertical motion. wR" denotes right side
of test panel when looking forward
"L" and "R" denote left and right side respectively of the test
panel when looking forward. Minus indicates up load. At this
station loads are applied 13.05 inches aft of the quarter
chard line
Same as preceding footnote except at this station loads are
applied 9.05 inches aft of the quarter chord line
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Table 4
Unsymmetrical Load Schedule*
Wing Aspect Ratio = 8.15
Station** 20% of Load 40% of Load 60% of Load 80% of Load 100% of Load
In Pounds In Pounds In Pounds In Pounds In Pounds
5.9 10
6.5 25 30
7.3 5 20
9.0*** 176R 352R 529R 705R
14.0****
-5.8L
-11.6L
-17,4L
-23.2L
5,8R
11.6R
17.4R
23.2R
17.7
10
19.2
20.5
5
20
25
29.6
10
3,3.4
25
37.0
5
20
42.1
10
-10L
20R
-15L
20R
Continued on following page
-ZOL
2OR
881R
-29L
29R
-25L
25R
30
All loads applied along the quarter chord except as noted
Measured in spanwise direction from test panel centerline in inches
Station at outside edge of center support. Load at this point
applied by restraining vertical motion. "R" denotes right side
of test panel when looking forward.
"L" and "R" denote left and right side respectively of the test
panel when looking forward. Minus indicates up load. At this
station loads are applied 14.1 inches aft of the quarter chora line
Same as preceding footnote except at this station loads are
applied 12.7 inches aft of the quarter chord line
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Continuation of Table L.
Unsymmetrical Load Schedule*
Wing Aspect Ratio = 8.15
Station** 20% of Load
In Pounds
51.2 5
40%� of Load
In Pounds
60% of Load 80% of Load
In Pounds In Pounds
100% of Load
In Pounds
54.3
10
20
60.2
30
64.0
25
66.5
5
68.0
10
70.7
20
75.1
30
81.3
5
10
25
5L
10L
15L
20L
25L
-5R
-10R
-15R
0-.20R
-25R
90.1
20
30
97.2
5
10
25
110.0
20
30
114.0
10
114.2****
5.81,
11.6L
17.4L
23.2L
29L
-5.8R
-11.6R
-17.4R
-23.2R
-29R
119.5
5
26
127.5
3
Total Load On
Specimen
80
186
294
402
510
All loads applied along the quarter chord line except as noted
** Measured in spanwise direction from test panel centerline in inches
*** "L" and "R" denote left and right side respectively of the test
panel when looking forward. Minus indicates up load. At this
station loads are applied 10.7 inches aft of the quarter chord line
***** Same as preceding footnote except at this station loads are applied
9.4 inches aft of the quarter chord line.
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TEST PROCEDURE
Reference is made to the photographs on pages 122 through :04 for the
method of loaddapplication and the test jig used. The test procedure
consisted of first marking the test specimen with masking tape at locations
defining the load application points and attaching scales to the bottom of
the test panel so that both torsional and bending deflection readings could
be made. The location of these scale attachment points is shown in Figures
17 and 18.
Following this, the specimen was placed in the test jig, rasied, and
warp readings recorded for the specimen at the internal pressure under
consideration. The test panel was then lowered to the supporting structure
of the test jig and the lowest load increment applied. Readings of the
scales were taken while the specimen was on the test jig supporting structure.
The specimen was then raised until clear of all supporting structure and new
readings taken. After reduction of these three sets of readings, the
deflection curve for the test panel was obtained. For all load increments
at the pressure under consideration, the procedure just described with respect
to readings was repeated with the exception that new warp readings were not
taken. To get the deflection curves for different internal pressures, it
was necessary to repeat the preceding procedure with the exception of the
specimen marking and scale attachment.
Two sets of readings were taken to check the contour stability of the
large Fortisan test panel while under an internal pressure of forty pounds
per square inah. The test panel was placed on two tables twenty-two inches
apart. The centerline of the test panel was made to coincide with the
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midline of the twenty-two inches between the tables. Five readings along
the centerline of both the top and bottom of the specimen were taken for
zero, sixty, and one-hundred and twenty pound loadings. The sixty and one
hundred and twenty pound loads were distributed along this centerline.
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40.0"
"L" and "R. denote left and right
side respectively when looking forward
Scale Location
(Aspect R4-Alo 8.15)
Tqzure 1?
and "R" dsrte
left and
Ade resperAively
ehsn lookflg
forward,
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TEST RESULTS
The test results are presented in two different forms in Appendices
"A" and "B". In appendix "A" are tables 6 through 37, in which the measured
data and its reduction for the test panels are shown. Also in this section
are tables 38 through 41 showing the conversion of deflections for some
of the test specimens to the corresponding values for the simulated wing.
Appendix "B" are Figures 20 through 33 which graphically dhow the test
specimen deflections. Also graphically presented in Figure 34 through 36
are some deflection curves to indicate internal pressure and cover ply
material effects. The deflections which could be expected of the simulated
wings are shown in Figures 37 through.40.
The measured values of the deflections were not entirely symmetrical.
This can be attriated to two major sources. The first is the cover ply
layups which were evidently not under a constant tension when they were
attached to the airmat. As a result, the stiffness of the cover plys
varied over the span length. The second source of error was the initial
warp of the specimens. This error was undoubtedly reduced considerably
by obtaining initial warp readings under zero external loads and correct-
ing the deflections accordingly.
A total of thirty different tests were run for this program. This
was the maximum number of tests which could be run in the short calendar
time allotted Since a complete envelope of test results covering all
internal pressures and loadings for the specimen could not be obtained,
it was necessary to choose which tests were to be run. For this reason
specimens were, shortly after receipt and with only a few tests performed,
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sent to the Fiberglas Department to be covered. The Dacron test panel,
representing the wing with an aspect ratio of 3.70, was damaged and could
not be tested because it was cured at too high a temperature and internal
pressure. The other Fiberglas covered specimen yielded results up to
60, of the maximum symmetrical load. At 80% of the maximum symmetrical
load a shear failure in the Fiberglas skin at the wing root connection
prevented continuation of the test.
The Fortisan covered specimen, represeinting the wing with the 8.15
aspect ratio, deflected at 15% of the maximum symmetrical load so much
that it wasn't considered necessary to continue the tests on this specimen
for any higher percentages of the maximum symmetrical load.
The results of the contour stability check are shown below in Figure 19
and Table 5.
1T 2T
1B ;4'1 3B
.13"
411
ilB
Crosoction Of
Test Panel
Contour Stabi-it7 Check
Figure 19
Unloaded
Cross-Sectional
Shape
Cross-Se.rfcn
60 PC�.").TA
arose-SeeVional
Shape .;kt
120 Fount: Load
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Table 5
Contour Change of
Fortisan Specimen
at 40 PSI Internal Pressure
Station*
Reading for
Zero Loading
Reading for
60 Pound
Loading
Reading for
120 Pound
Loading
Deflection
for 60 Pound
Loading
Deflection
for 120 Pound
Loading
1T
6.38
6.41
6.44
.03
.06
2T
7.12
7.22
7.33
.10
.21
3T
7.56
7.69
7.84
.13
.28
4T
7.31
7.42
7.53
.11
.22
5T
6.88
6.84
6.80
.04
.08
IB
4.19
4.16
4.13
.03
.06
2B
3.28
3.18
3.07
.10
.21
3B
3.08
2.96
2.82
.12
.26
4B
3.13
3.02
2.91
.11
.22
5B
3.47
3.43
3.39
.04
.08
*Reference Figure 19.
It was not possible to actually simulate a wing cross-section, because
the leading and trailing edge radii of the test panel have a shape stiffness
whereas a comparable stiffness does not exist in the NAGA 66-010 airfoil.
The results of the contour check on the test panel merely indicate this
leading and trailing edge stiffness and it is probable that even smaller
contour deviations would occur on an airfoil shape.
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CONCLUSIONS AND RECOMMENDATIONS
The test results obtained show the structural feasibility of using
airmat, in some form, as an airframe material for an aircraft capable of
flying under the loads and at the speeds described in the aerodynamic section
of this report.
For wings with an aspect ratio of four of less, airmat in its simplest
form will meet the structural requirements. The deflections measured in
this test for the wing with the 3.70 aspect ratio are considerably more
severe than a wing on an airplane would experience. This is because the
airplane wing would have a better mass distribution; that is, weight in
the form of nacelles properly located on the wing which would reduce the
deflections.
High aspect ratio wings made of airmat employing fiberglas as a cover
ply material and epoxy resins as the bonding agent are very stiff and thus
feasible from the structural viewpoint. In a comparison of this wing
construction and a fiberglas wing having a foam core, the airmat wing with
the fiberglas cover plys should be lighter. In the airmat wing, better
utilization may be made of the fiberglas strength. The reason for this is
the elimination of buckling under compression as a problem and the ability
to make full use of the high tensile strength of fiberglas. In the fiberglas
covered airmat wing, the air plus the drop threads and the single nylon
rubber impregnated cover ply would probably be lighter than the comparable
fo.;1 core needed to stabilize the compression side of the fiberglas wing.
From these tests, the general conclusion may also be drawn that the
stiffness of an airmat structure increases with the internal pressure.
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This suggests the possible use of conical shaped fabric spars under high
internal pressures for achieving stiffness in conjunction with lightweight
airmat for maintaining the airfoil shape.
Another possibility for obtaining a very stiff airmat structure is
through the use of fiberglas cloth with a neoprene bonding agent, thereby
taking advantage of the stiffness qualities of fiberglas yet yielding a
material with limited folding capabilities.
Some further development work would be required for any of these
suggested methods to yield optimum results with respect to strength, stiffness,
weight and radar reflectivity. It should be noted though, that on the
basis of the test results presented in this report, the success of such a
development program seems assured.
With this in mind, and as a first step, it is recommended that a
parametric study, encompassing the missich requirements and the suggested
structures, be initiated.
The results of such a parametric study should further substantiate
the feasibility of using airmat, in some form, as the airframe material
for a high speed, high altitude reconnaisance airplane.
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APPENDIX A
TEST RESULTS IN
TABULAR FORM
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EXPLANATION OF COLUMN. HEADINGS FOR DEFLECTION TABUS
SYMMETRICAL LOADINGS
Points where deflections measured, reference Figures 17 and 18 on
page 52 .
Zero readings taken when specimen loaded but resting on jig supporting
structure.
G") Loaded readings taken when specimen loaded and rasied clear of jig support-
ing structure.
0 Difference of columns one and two which represent deflections plus initial
warp of structure measured with respect to transit level.
Initial warp of specimen measured with-respect to a plane through the
specimen centerline. Reference Tables 6 and 7 on pages 62 and 63 .
(H) Summation of cblumns four and five which eliminates the initial warp of
the specimen from the deflection readings.
Subtraction of the deflection reading at point nine, column six, from
the deflection readings at all odd numbered points in column six.
Substraction of the reading at point ten from the readings at all even
numbered points in column six. This operation changes the deflection
reference plane from the transit level to a plane through the specimen
centerline.
Subtraction of the sum of the two tip deflections at one end from the sum
of the two tip deflections at the other end of column seven divided by
two represents the average difference between the tip deflections.
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Division of this average difference between the tip deflections by the
span length is the tangent of the angle through which the deflection
reference plane should be rotated to make the center support level.
Correction of all the deflection readings of column seven are made by
the addition or substraction of the factor obtained by multiplying the
distance from the centerline by the tangent of the angle through which
the deflection reference plane should be rotated.
60
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EXPLANATION OF COLUMN HEADINGS FOR DEFLECTION TABLES
UNSYMMETRICAL LOADINGS
Points where deflections measured, reference Figures 17=d 18 on
page 52 .
Zero readings taken when specimen loaded with symmetrical portion of
load but resting on jig supporting structure.
Loaded readings taken when specimen loaded with both symmetrical and
antisymmetrical portion of load and rasied clekr of jig supporting
structure.
Difference of columns one and two which represent deflections plus
initial warp of structure measured with respect to transit level.
Initial warp of specimen measured with respect to a plane through the
specimen centerline. Reference Tables 6 and 7 on pages 62 and 63 .
Summation of columns four and five which eliminates the initial warp
of the specimen from the deflection readings.
Subtraction of the deflection reading at point nine, column six, from
the deflection readings at all odd numbered points in coluMn six.
Subtraction of the readings at point ten from the readings at all ev0
numbered points in column six. This operation changes the deflection
reference plane from the transit level to a plane through the specimen
centerline.
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Table 6
Warp Readings
Wing Aspect Ratio = 8.15
Station*** 20 PSI* 40 PSI** 60 PSI **
Corrected
*****
1
2
3
4
5
6
7
8
9
1.0
11
12
13
14
15
16
17
18
* Cover Ply Material - Dacron with Fiberglas
** Cover Ply-Material - Fortisan
*** Reference Figure 17
**** Reading taken with scale against bottom of specimen.
Specimen raised clear of test jig with no load on it.
***** Deflection reference plane moved from transit level to a
plane through the centerline of the specimen.
Reg
Corrected
*****
Reading
Corrected
*****
Reading
*w**
18.10
-.70
7.95
+9.60
7.70
18.10
-.70
8.70
+8.85
8.55
17.90
-.50
11.32
+6.23
9.90
17.85
-.45
11.74
+5.81
11.10
17.50
-.10
14.20
+3.35
11.55
17.50
+.10
15.50
+2.0
12.95
17.30
+.10
16.70
+.85
13.15
17.18
+.22
17.15
+.40
13.95
17.40
o
17.55
o
14.60
17.40
o
17.55
o
14.75
17.10
+.30
18.20
-.65
17.05
17.30
+.10
16.75
+.80
15.60
16.70
+.70
20.10
-2.55
22.30
17.45
-.05
17.50
+.05
19.60
16.60
+.80
23.40
-5.85
29.90
17.40
0
21.80
-3.25
27.70
17.40
0
27.55
-10.00
35.50
17.40
o
27.75
-10.20
37.70
_6.90
-6.2o
_4.70
-3.65
-2.0
-1.80
-1.45
- 8
0
+2.45
+.85
+7.70
+4.85
+15.30
+12.95
+22.90
+22.95
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Table 7
Warp Readings
Wing Aspect Ratio = 3.70
Station***
20 PSI*
Reading Corrected
40 PSI*
Reading Corrected
60 PSI**
Reading Corrected
****
*****
****
*****
****
*****
1
21.49
-.06
2140
-.10
15.60
+4.85
2
21.46
....co
20.95
-.15
15.50
+4.50
3
20.63
-.92
20.39
-.71
16.60
+3.55
4
20.53
-1.02
20.08
-1.15
17.08
+2.98
5
20.48
-1.07
20.03
-.60
18.30
+2.15
6
20.35
-1.20
19.90
-1.21
18.90
+1.10
7
21.07
...48
20.71
-.39
19.60
+.85
8
20.99
-.56
20.68
-.42
20.05
-.05
9
21.55
0
21.10
0
20.45
0
10
21.55
0
21.10
0
20.00
0
11
22.09
+,:54
21.49
+.39
21.10
-.65
12
22.11
+.56
21..52
+.42
19.90
+.10
13
22.62
+1.07
21.70
+.60
22.00
-1.55
14
22.75
+1.20
22.31
+1.21
20.55
-.55
15
22.91
+1.36
21.81
+.71
23.50
16
22.57
+1.02
22.0
+.95
22.55
-2.55
17
21.59
+.04
21.17
+,.07
25.45
-5.00
18
21.66
+.11
21.26
+.16
25.40
-5.40
Cover Ply Material - Dacron
Cover Ply Material - Fortisan
Reference Figure 18
Reading taken with scale against bottom of specimen.
Specimen raised clear of test jig with no load on it.
Deflection reference plane moved from transit level to a
plane through the centerline of the specimen.
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Table No.8
Wing Aspect Ratio = 3.70
20% of Maximum Symmetrical Load
at 20 PSI Internal Pressure
Cover Ply Material - Dacron
1
3.25
1.42
2
4.12
2.55
3
3.10
4.58
4
4.10
5.93
**5
-19.85
-11.30
**6
-20.15
-10.90
**7
-16.20
- 3.80
8
3.00
9.53
**9
-13.40
- 1.30
*4,10
-21.00
- 5.70
**11
-19.65
- 4.50
**12
-17.80
- 2.20
*'13
-14.80
- .20
14
5.40
"i12.85
15
5.60
11.96
16
4.68
11.76
17
5.32
12.05
18
3.40
10.48
-1.83 -.06 -1.89
-1.57 -.09 -1.66
1.48 -.92 - .56
1.83 -1.02 - .81
4.28 -1.07 3.21
4.62 -1.20 3.42
6.20 - .48 5.72
6.53 - .56 5.97
7.35 0 7.35
7.65 0 7.65
7.58 + .54 8.12
7.80 + .56 8.36
7.30 +1.07 8.37
7.45 +1.20 8.65
6.36 +1.36 7.72
7.08 +1.02 8.10
6.73 + .04 6.77
7.08 + .11 7.19
-9.24
-4.86
-9.31
-4.93
-6.79
-3.21
-6.84
-3.26
-4.14
-1.55
-4.23
-1.64
-1.63
- .41
-1.68
- .46
0
0
0
0
+ .77
- .45
+ .71
- .51
+1.02
-1.57
+1.00
-1.59
+ .37
-3.21
+ .45
-3.13
- .58
-4.96
- .46
-4.84
*Reference page 59 for explanation of column headings.
**These soales were half-scale and inverted.
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**5
_20.35
-9.95
**6
-21.05
-9.60
**7
-16.50
- .80
8
2.61
-11.81
*49
-13.50
+5.00
**10
-21.68
-2.06
**11
-19.75
-1.45
**12
-17.70
+1.00
**13
-14.70
+1.40
14
5.40
1.60
15
5.64
12.40
16
4.68
11.54
17
5.30
10.85
18
3.36
8.98
SECRET
GOODIVIEAR
AIRCRAFT
GEE 8499
Table No, 9
Wing Aspect Ratio = 3.70
40% of Maximum Symmetrical Load
at 20 PSI Internal Pressure
Cover Ply Material - Dacron
0 *
0 * 0* 0 * 0* 0 * 0* 0 *
1 3.22 0 -3.22 -.06 -3.28 -12.53 - 8.08
2 4.04 .92 -3.12 -.09 -3.21 -13.02 - 8.57
3 2.81 4.20 1.39 -.92 .47 - 8.78 - 5.14
4 3.78 5.60 1.82 -1.02 .80 - 9.01 - 5.37
5.21 -1.07 4.14 - 5.11 - 2.48
5.73 -1.20 4.53 - 5.28 - 2.65
7�85 - .48 7.37 - 1.88 - .64
9,20 - .56 8.64 - 1.17 + .07
9.25 0 9.25
9.81 0 9.81
9.14 + .54 9.68
9.35 + .56 9.91
8.05 +1.07 9.12
8.20 +1.20 9.40
6.76 +1.36 8.12
6.86 +1.02 7.88
5.55 + .04 5.59
5.62 + .11 5.73
0
0
0
0
+ .43
- .81
+ 1.10
- .14
- .13
- 2.76
- .41
3.04
- 1.13
- 4.77
- 1.93
_ 5.57
- 3.66
- 8.11
- 4.08
- 8.53
*Reference page 59 for explanation of column headings.
**These scales were half-scale and inverted.
SECRET
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65
Approved for Release: 2019/04/09 CO2014934
SECRET GooDlirEAR
AdFOLArr
GER 8499
Table No. 10 .
Wing Aspect Ratio 3.70
60% of Maximum Symmetrical Load
at 20 PSI Internal Pressure
Cover Ply Material Dacron
0 * * 0 * 0* 0 * 0* 0 * *
1 3.01 .60 -2.48 -.60 -2.54 -16.19 -12.44
2 4.00 .90 -3.10 -.09 -3.19 _17.49 -13.74
3 2.74
4 3.80
**5
-20.48
**6
-21.10
**7
-16.70
8
2.61
**9
-13.70
**10
-22.00
**Ia.
-19.75
**12
-18.00
**13
_14.70
14
5.40
15
3.32
16
4.76
17
5.30
18
3.88
6.00
3.26
7.30
3.50
-3.70
8.37
-3.70
8.70
+7.30
12.00
14.98
12.37
+13.60
13.65
+ 6.60
14.30
+ 6.10
12.93
+ 8.50
13.25
+ 5.40
10.05
4.20
10.80
11.40
8.08
12.60
7.84
10.15
4.85
8.65
4.27
-.92 2.34 -11.31 - 8.24
-1.02 2.48 -11.82 - 8.75
-1.07 7.30 - 6.35 - 4.13
-1.20 7.50 - 6.80 - 4.58
- .48 11.52 - 2.13 - 1.09
- .56 11.81 - 2.49 - 1.45
0 13.65 0 0
o 14.30 0
+ .54 13.47 - .1p - 1.22
+ .56 13.81 _ .49 _ 1.53
+1.07 11.12 - 2.53 - 4.75
+1.20 12.00 - 2.30 - 4.52
+1.36 9.44 - 4.21 - 7.28
+1,02 8.86 - 5.44 - 8.51
+ .04 4.89 - 8.76 -12.51
+ .11 4.38 - 9.92 -13.67
*Reference page 59 for explanation of column headings.
**These scales were half-scale and inverted.
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Approved for Release: 2019/04/09 CO2014934
**5
-20.10
-6.50
**6
-21.30
-5.10
**7
-15.95
+2.75
8
2.75
12.30
**9
-13.00
+7.00
"10
-21.00
+ .10
**11
-19.30
- .90
**12
-17.28
+1.55
**13
-15.35
- .60
14
4.66
12.20
15
3.16
8.36
16
3.17
8.26
17
3.94
7.20
18
4.10
7.00
SECRET
G000"(EAR
AIRCRAFT
GER 8499
Table No. 11
Wing Aspect Ratio := 3.70
40% of Maximum Symmetrical Load
at 40 PSI Internal Pressure
Cover Ply Material - Dacron
0 * 0* 0* 0* 0* 0*
1 3.20 3.40 .20 -.10 .10
2 3.70 3.60 -.10 -.15 -.25
3 2.90 6.95 4.05 -.71 3.34
4 3.52 8.20 4.68 -1.15 3.53
6.80 - .60 6.20
8.10 -1.21 6.89
9.35 - .39 8.96
9.55 - .42 9.13
10.00 0 10.00 0 0
10.16 0 10.16 0 0
9.20
9.42
7.37
7.54
5.20
5.09
3.26
2.90
*Reference page 59 for explanation of column headings.
**These sca1ds were half-scale and inverted.
0*
0*
-9.90
-8.26
-10.41
-8.77
- 6.66
-5.32
- 6.63
-5.29
- 3.80
-2.83
- 3.27
-2.30
- 1.04
- .59
- 1.03
- .58
+ .39
9.59
.41
- .86
+ .42
9.84
- .32
- .77
+ .60
7097
- 2.03
3.00
+1.21
8.75
.. 1.41
-2.38
+ .71
5.91
- 4.09
-5.43
+ .95
6.04
- 4.12
-5.46
+ .07
3.33
- 6.67
-8.31
+ .16
3.06
- 7.10
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67
Approved for Release: 2019/04/09 CO2014934
**5
-19.90
**6
-21.40
**7
_15.80
8
2.70
**9
_12.90
**10
-19.55
**11
-19.10
**12
-17.30
**13
-.15.2
14
5.38
15
3.90
16
3.95
17
3.90
18
4.14
SECRET
GOODAEAR
AIRCRAFT
GER 81499
Table No, 12
Wing Aspect Ratio = 3.70
60% of Maximum Symmetrical Load
at 40 PSI Internal Pressure
Cover Ply Material - Dacron
0 * 0* 0 * 0* 0 * (F)* 0 * (H) *
1 3.25 4.65 1.40 -.10 1.30 41.80 -11.23
2 3.60 4.80 1.20 -.15 1.15 -12.62 -12.05
3 2.90 8.96 6.06 -.71 5.35 -7.75 -7.28
4 3.42 10.20 6.77 -1.15 5.63 -8.14 -7.67
-.10 9.90 -.60 9.30 -3.80 _3.46
�,20
9.10
15.81
13.3
6.45
4.35
7.50
2.9
14.60
8.95
8.95
6.20
6.35
10.80
-1.21
12.45
_.39
13.11
-.42
13.10
0
13.77
0
11.72
+.39
12.40
+.42
9.05
+.60
9.22
+1.21
5.05
+.71
5.00
+.95
2.30
+.07
2.21
+.16
9.59 -4.18 -3.84
12.06 -1.04 -.88
12.69 _1.08 -.92
13.10 0 0
13.77 0 0
12.11 -.99 -1.15
12.82 -.95 -1.11
9.65 -3.45 -3.79
10.43 -3.34 -3.68
5.76 -7.34 -7.81
5.95 -7.82 -8.29
2.37 -10.73 -11.30
2.37 -11.40 -11.97
*Reference page 59 for explanation of column headings.
**These scales were half-scale inverted.
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Approved for Release: 2019/04/09 CO2014934
SECRET
GOODAfEAR
AIRCRAFT
GER 8499
Table No. 13
Wing Aspect Ratio = 3.70
80% of Maximum Symmotrical Load
at 40 PSI Internal Pressure
Cover Ply Material - Dacron
(7)* 0 * Ci) * 0* 0*
0 * 0 * 0 *
1 3.23
2 3.80
3 2.91
4 3.68
"5
-20.25
**6
-21.10
"7
-.16.40
8
2.66
"9
-13.6
**10
-21.65
**11
-19.70
**12
-17.80
**13
--15.10
14
5.36
15
3.26
16
3.40
17
4.04
18
4.35
3.50
.27
3.65
-.15
8.75
5.84
10.05
6.37
1.00
10.62
1.35
11.22
11.10
13.75
16.84
14.18
15.35
14.52
8.55
15.10
5.30
12.50
8.70
13.25
2.60
8.85
14.20
8.84
7.45
4.19
7.48
4.08
3.35
-.69
3.1
-1.25
-.10 .17 -14.35 -14.75
-.15 -.30 -15.39 -15.79
-.71 5.13 9.39 - 9.71
-1.15 5.22 - 4.87 -10.19
- .60 10.02 - 4.50 4.73
-1.21 10.01 - 5.08 - 5.31
- .39 13.36 1.16 - 1.27
- .42 13.76 1.33 - 1.44
0 14.52 0 0
0 15.10 o o
+ .39 12.89 - 1.63 - 1.52
+ .42 13.67 - 1.42 - 1.31
+ .60 9.45 - 5.07 - 4.84
+1.21 10.05 - 5.04 - 4.81
+ .71 4.90 - 9.62 - 9.30
+ .95 5.03 -10.06 - 9.74
+ .07 -.62 -15.14 -14.74
+ .16 -1.09 -16.18 -15.78
*Reference page 59 for explanation of column headings.
**These scales were half-scale inverted.
69
SECRET
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Approved for Release: 2019/04/09 CO2014934
SECRET GOODANEAR
AIRCRAFT
GER 8499
Table No. 14
Wing Aspect Ratio = 3.70
100% of Maximum Symmetrical Load
at 40 PSI Internal Pressure
Cover Ply Material - Dacron
0 * 0* 0 * * 0* 0 * 0* 0 *
1 3.18 4.40 1.22 -.10 1.12 -18.68 -18.92
2 3.20 4.35 1.15 -.15 1.00 -18.06 -18.30
3 2.90 10.56 7.66 -.71 6.95 -10.85 -11.05
4 3.20 11.82 8.62 -1.15 7.47 -11.59 -11.79
**5
-19.65
6.70
**6
-21.90
7.00
**7
-15.4
1811
8
2.46
20.52
**9
-12.5
23.1
**lo
-17.3
14.8
**11
-18.80
12.10
**12
--17.9
14.8
**13
-14.9
6.80
14
5.16
16.5
15
3.34
8.65
16
3.20
8.55
17
4.00
3.15
18
4.14
3.4
13.18
14.45
16.75
18.06
17.80
19.06
15.45
16.35
10.85
10.34
5.31
5.35
-.85
-.74
- .60
-1.21
12.58
13.24
- 5.22
- 5.82
- 5.36
- 5.96
- .39
16.36
- 1.44
- 1.51
- .42
17.62
- 1.44
- 1.51
0
17.80
0
0
0(
19.06
0
o
+ .39
15.84
-1,96
1.89
4- .42
16.77
- 2.29
- 2.22
+ .60
11.45
- 6.35
6.21
+1.21
11.55
- 7.51
- 7.37
+ .71
6.02
-11.78
-11.58
4- .95
6.30
12.76
-12.56
+ .07
-.78
-18.58
-18.34
+ .16
-.58
-19.64
-19.40
*Reference page 59 for explanation of column headings.
**These scales were half-scale and inverted.
SECRET
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70
Approved for Release: 2019/04/09 CO2014934
SECRET GooDAEAR
AIRCRAFT
GER 8499
Table No. 15
Wing Aspect Ratio =1,3.70
20% of Maximum Symmetrical Load
at 60 PSI Internal Pressure
Cover Ply Material - Fortisan
c)* o* (T)* 20*
23.0 17.0
23.61 17.71
23.00 18.48
25.58 19.26
24.66 19.85
28.10 21.04
29.12 21.13
27.78 21.26
32.00 21.76
27.82 21.76
31.16 22.08
25.64 21.33
32,92 22.66
25.88 21.48
28.13 23.33
26.33 22.81
30.80 24.78
31.66 25.16
1
6.00
2
5.90
3
4.52
4
6.32
5
-15.04
6
-13.98
7
-13.14
8
6.52
9
-11.52
lo
-15.70
11
-13.00
12
-17.02
13
-12.40
14
4.40
15
4.80
16
3,52
17
6.02
18
6.50
4.85
21.88
.12
-1.02
4.50
22.21
.45
-.69
3.55
22.0
.27
--.59
2.98
22.24
.48
-.38
2.15
22.00
.24
-.33
1.10
22..14
.38
-.19
.85
21.98
.22
-.05
21.21
..55
-.27
21.76
0
0
21.76
-.65
21.43
-4.33
-.05
+.10
21.43
-.33
-.0
-1.55
21.11
-.65
-.08
-.55
20.93
-.83
-.26
-3.0
20.28
-1.48
-.62
-2.55
20.26
-1.50
-.64
-5.00
19.78
-1.98
-.84
-5.40
19.76
-2.00,.
-.86
*Reference page 59 for explanation of column headings.
SECRET
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Approved for Release: 2019/04/09 CO2014934
SECRET GOODAEAR
AIRCRAFT
GER 8499
Table No, 16
Wing Aspect Ratio = 3.70
40% of Maximum Symmetrical Load
at 60 PSI Internal Pressure
Cover Ply Material - Fprtisan
0 * * 0 * *
* 0 *
1
6.02
2
5.90
3
4.54
4
6.33
5
-15.02
6
-13.96
7
-13.10
8
6.54
9
-11.50
10
-15.68
11
-12.98
12
-17.00
13
-12.40
14
4.40
15
4.81
16
3.52
111
6.03
18
6.50
21.50
22.00
22.19
24.68
24.58
27.84
30.50
29.09
34.20
30.02
33.72
28.10
35,00
26.95
29.06
27.27
31.58
32.35
�
15.48
4.85
20.33
-2.52
16.10
4.50
20.60
-2.25
17.65
3.55
21.20
-1.65
18.35
2.98
21.33
-1.52
19.80
2.15
21.95
-.90
20.90
1.10
22.00
-.85
21.80
.85
22.65
-.20
22.55
-.05
22.50
-.35
22.85
0
22.85
0
22.85
0
22.85
0
23.35
-.65
22.70
-.15
22.55
.10
22.65
-.20
23.70
-1.55
22.15
-.70
22.55
-.55
22.00
-.85
24.25
-3.05
21.20
-1.65
23.75
-2.55
21.20
-1.65
25.55
-5.00
20.55
-2.30
25.85
-5.40
20.45
-2.40
*Reference page 59 for explanation of column headings.
-2.50
.2.23
-1.64
-1.51
-.89
-.84
-.20
-.35
0
0
-.15
-.20
-.71
-.86
-1.65
-1.66
-2.32
-2.42
SECRET
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72
Approved for Release: 2019/04/09 CO2014934
SECRET
GOOD/EAR
AIRCRAFT
GER 8499
Table No. 17
Wing Aspect Ratio = 3.70
60% of Maximum Symmetrical Load
at 60 PSI Internal Pressure
Cover Ply Material Fprtisan
0* 0* 0* 0* 0* CD*
1 6.03 20.63 14.60 4.85
2 5.91 20.96 15.05 4.80
3 4.56 22.12 17.55 3.55
4 6.34 24.68 18.35 2.98
5 -15.00 26.00 20.50 2.15
6 -13.96 28.90 21.43 1.10
7 -13.08 32.72 22.90 .85
8 6.55 30.10 23.55 -.05
9 -11.50 36.60 24.05 0
10 -15.68 32.42 24.05 0
11 -12.96 35.74 24.35 -.65
12 -16.98 30.12 23.55 .10
13 -12.38 36.10 24.24 -1.55
14 4.41 27.56 23.15 -.55
15 4.82 29.12 24.30 -3.05
16 3.53 27.28 23.75 -2.55
17 6.04 30.59 24.55 -5.00
18 6.51 31.36 24.85 -5.40
19.45
-4.60
-4.60
19.55
-4.50
-4.50
21.10
_2.95
-2.95
21.33
-2.72
-2.72
22.65
-1.40
-1.40
22.53
-1.52
-1.52
23.75
-.30
-.30
23.50
-.55
-.55
24.05
0
0
24.05
0
0
23.70
-.35
-.35
23.65
-.40
-.40
22.69
-1.36
-1,36
22.60
-1.45
-1.45
21.25
-2.80
-2.80
21.20
-2.85
-2.85
19.55
-4.50
-4.50
19.45
-4.60
-4.60
*Reference page 59 for explanation of column headings.
SECRET
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73
Approved for Release: 2019/04/09 CO2014934
SECRET
tOoDIVEAR
AIRCRAFT
GER 8499
Table No. 18
Wing Aspect Ratio = 3.70
80% of Maximum Symmetrical Load
at 60 PSI Internal Pressure
Cover Ply Material - Fortisan
� � . 0 . 0.
1
6.05
20.36
2
5.93
20.54
3
4.57
22.63
4
6.35
24.78
5
-14.98
27.84
6
-13.94
30.66
7
-13.06
35.86
8
6.57
31.53
9
-11.48
40.00
10
-15.66
35.82
11
-12.94
38.78
12
-16.96
33.26
13
-12.38
38.08
14
4.42
28.4$
15
4.83
29.39
16
3.54
27,40
17
6.05
29.86
18
6.52
30.43
0*
c)*
1.4.31 4.85 19.16 -6.58 -6.82
14.61 4.00._ 19.11 -6.63 -6.87
18.06 3.55 21.61 -4.13 -4.31
18.44 2.98 21.42 -4.32
21.41 2.15 23.56 -2.18 7-2.30
22.30 1.10 23.40 -2.34
24.46 .85, 25.31 -43 -.49
24.96 -.05 24.91 _.83 -.89
25.74 o 25.74 0 o
25.74 0 25.74 0 o
25.86 -.65 25.21
25.11 .10 25.21
25.231 r;
_.� 23.68
24.06 ,55 25.51
24.56 -3.05 21.51
23,86 -2.55 21.31
23.81 -540 18.81
23.91 -5.40 18.51
*Reference page 59 for explanation of column heading.
-.53
-053
-.47
-.47
-2.06
-1.96
.-2.23
..2.09
-4.23
-4.05
-4.43
-4.25
-6.93
-6.69
-7.23
-6.99
SECRET
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Approved for Release: 2019/04/09 CO2014934
SECRET
GooDfirEAR
AIRCRAFT
GER 8499
Table No, 19
Wing Aspect Ratio = 3.70
100% of Maximum Symmetrical Load
at 60 PSI Internal Pressure
Cover Ply Material - Fortisan
0 * 0* 0* 0* * 0*
6.07 28.06 11.99 4.85 16.84 -10.14 -8.22
2 5.95 27.98 12.03 4.00 16.53 -10.45 -8.53
3 4.03 31.16 16.57 3.55 20.12 -6.87 -5.43
4 6.36 33.25 16.89 2.98 19.87 4.11 -5.67
5 -14.96 27.12 21.04 2.15 23.19 -.3.79 -2.83
6 -13.92 29.94 21.93 1.10 23.07 .-3.95 -2.99
7 -13.04 37.08 25.06 .85 25.91 -.1.07 .459
8 6.58 32.21 25.63 -.05 25.58 -1.40 -.92
9 -11.46 42.50 26.98 0 26.98 0 0
10 -15.64 38.32 26.98 0 26.98 0 0
11 -12.92 41.46 27.19 -.65 26.54 -.44 -.92
12 -16.94 36.12 26.53 .10 26.63 -.35 -.83
13 -12.36 41078 26.57 -1.55 25.02 -1.96 -2.92
14 4.43 29.86 25.43 ...55 24.88 -2.10 -3.06
15 4.84 30.73 25.89 -3.05 22.84 .4.14 -5.58
16 3.55 28.88 25.33 -2.55 22.78 -11.20 -5.64
17 6.06 31.75 25.69 -5.00 2069. -6.29 -8,21
18 6.52 32.30 25.78 -5.40 2038 -6.60 -8.52
*Reference page 59 for explanation of column headings.
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SECRET
GOODAEAR
AIRCRAFT
GER 8499
Table No. 20
Wing Aspect Ratio = 3.70
20% of Unsymmetrical Load
at 60 PSI Internal Pressurel
Cover Ply-Material - Fortiaan
3 *
1
6.00
21.25
2
5.88
21.68
3
4.50
21.10
4
6,30
23.60
5
_15.06
20.54
6
-14.00
24.04
7
-13.16
24.54
8
6,50
25.88
9
-11.50
28.00
10
-15.70
23.80
11
-13.02
27.98
12
-17.00
22.00
13
-12,40
29.90
14
4.41
24.46
15
4.t;31
2746
16
16
3.51
25.26
17
6.01
30.01
18
6.48
30.88
0 * (I)* 0* 0 *
15.25 4.85 20.10 .35
15.80 4.80 20.30 .55
16.60 3.55 20.15 .40
17,30 2.98 20.28 .53
17.80 2.15 19.95 .20
19.02 1.10 20.12 .37
18.85 .85 19,70 -.05
19.38 �-.05 19,33 -.42
19.75 0 19.75 0
19.75 0 19.75 0
20.50 -.65 19.85 .10
: 15
19.50 19.60 -.15
-1
21.15 19.60 -.15
20.05 -.55 19.50 -.25
22.25 -3.05
.75 19.20 -.5.5
5
-
2.55 19.20 -.55
24.00 _5.00 19.00 -.75
24.40 -5.40 19.00 -.75
*Reference: page 61 for explanation of column headings..
76
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SECRET
GOODAVIEAR
AIRCRAFT:
GER 8499
Table No. 21
Wing Aspect Ratio = 3.70
40% of Unsymmetrical Load
at 60 PSI Internal Pressure
Cover Ply Material - Fortisan
* * 0 * 0 * 0 * 0 *
1
6.01
22.37
2
5.88
22.39
3
4,48
22.19
4
6.28
24.44
5
-15.10
22.82
6
-14.02
25.84
7
-13.18
27.04
8
6.48
27.36
9
_11.52
30.20
10
-15.72
2640
11
-13.04
29.78
12
-17.02
23.64
13
-12.42
30.80
14
4.40
24.93
15
4.80
27.34
16
3.49
25.22
17
6.00
29.81
18
6.46
30.34
16.36 4.85 21.21 .35
16,51 4.50 21.01 .15
17.71 3.55 21.g6 .40
18.16 2.98 21.14 .28
18.96 2.15 21.11 .25
19.93 1.10 21.03 .17
20.11 .85 20.96 .10
20.88 -.05 20.83 -.03
20.86 0 20.86 o
20.86 0 20.86 0
21.41 -.65 20.76 -.10
20.33 .10 20.43 -.43
21.81 -1.55 20.26 -.60
20.53 -055 19.98 -.88
22.54 -3.05 19.49 -1.37
21,73 -2.55 19.1a -1.68
23.81 -5.00 18.81 -2.05
23.88 -5.40 18.48 -2.38
*Reference page 61 for explanation of column headings.
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SECRET
GOODAEAR
AIRCRAFT
GER 8499
Table No. 22
Wing Aspect Ratio = 3.70
60% of Unsymmetrical Load
at 60 PSI Internal Pressure
Cover Ply Material - Fortisan
* 0* 0 0* 0* * 0 *
1 6.00 23.52 17.52 4.85 22.37 .35
2 5.87 23.62 17.75 4.00 22.25 .23
3 4.46 23.37 18.91 3.55 22.46 .44
4 6.26 25.52 19.26 2.98 22.24 .22
5 -15.12 25.6 20.19 2.15 22.34 .32
6 -14.04 28.04 21.04 1.10 22.14 .12
7 -13.20 29.36 21.28 .85 22.13 .11
8 6.47 28.55 22.08 -.05 22,03 .01
9 -11.54 32.60 22.02 0 22.02 o
10 -15.74 28.30 22.02 0 22.02 0
11 -13.06 31.56 22.31 -.65 21.66 -.36
12 -17.04 25.98 21.51 .10 21.61 -.41
13 -12.44 32.36 22.40 -1.55 20.85 -1.17
14 4.38 25.63 21.25 -.55 20.70 -1.32
15 4.78 27.4 22.68 -3.05 19.63 -2.39
16 3.48 25.46 21.98 -2.55 19.43 -2.59
17 5.99 29.46 23.47 -540 18.47 -3.55
18 6.45 30.04 23.59 -5.40 18.19 -3.83
*Reference page 61 for explanation of column headings,
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SECRET
GOODAVOIL
AIRCRAFT
GER 8499
Table No. 23
Wing Aspect Ratio = 3.70
80% of Unsymmetrical Load
at 60 PSI Internal Pressure
Cover Ply Material - Fortisan
1
5.99
25.46
19.47
4.85
24.32
.35
2
5.87
25.62
19.75
4.50
24.25
.28
3
4.46
25.33
20.87
3.55
24.42
.45
4
6.25
26.73
20.47
2.98
23.45
-.52
5
-15.14
27.60
21.32
2.15
23.47
-.50
6
-14.06
30.44
22.25
1.10
23.35
-.62
7
-13.22
31.62
22.42
.85
23.27
-.70
8
6.46
29.71
23.25
-.05
2 3.20
-.77
9
-11.54
36.50
23.97
0
23.97
0
10
-15.74
32.20
23.97
0
23.97
0
11
-13.08
35.06
24.07
-.65
2 3.42
-.55
12
-17.06
29.68
23.37
.10
23.47
-.50
13
-12.46
35.08
22.22
-1.75
14
4.37
27.12
22.20
-1.77
15
+.78
28.40
23.62
-3.05
2 0.57
-3.40
16
3.47
26.59
23.12
-2.55
20.57
-3.40
17
5.99
30.11
24.12
-5.00
19.12
-4.85
18
6.44
30.61
24.17
-5.40
18.77
-5.20
*Reference page 61 for explanation of column headings.
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GOODAEAR
AIRCRAFT
GER 8499
Table No. g4
Wing Aspect Ratio = 3,70
100% of Unsymmetrical Load
at 60 PSI Internal Fressilre
Cover Ply Material - Fortisan
G* 0* 0* 0* 0*
1
5.96
2
5.86
3
4.42
4
6.24
5
-15.19
6
_14.16
7
-13.26
8
6.43
9
-11.60
10
-15.80
11
-13.14
12
-17.06
13
-12.41
14
4.34
15
.72
16
3.43
17
5.95
18
6.43
26.12 20.16 4.85 25.01 .15
25.92 20.06 4.50 24.56 -.30
25.98 21.56 3.55 25.11 .25
27.95 21.71 2.98 24.69 -.17
30.93 23.06 2.15 25.21 .35
33.26 23.71 1.10 24.81 -.05
35.26 24.26 .85 25.11 .25
31.29 24.86 -.05 24.81 -.05
38.12 24.86 0 24.86 0
33.92 24.86 0 24.86 0
36.28 24.71 -.65 24.06 -.80
30.86 23.96 .10 24.06 -.80
35.01 23.71 -1.55 22.16 ;2.70
27.05 22.71 -.55 22.16 -2.70
23.48 22.76 -3.05 19.71 -5.15
25.59 2246 -2.55 19.61 -5.25
28.31 22.36 -5.00 17.36 -7.50
28.79 22.36 -5.40 16.96 -7.90
*Reference page 61 for explanation of column headings.
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SECRET GOOD/EAR
AIRCRAFT
GER 8499
Table No. 25
Wing Aspect Ratio 8.15
15% of Maximum Symmetrical Load
at 40 PSI internal Pressure
CoVer Ply Material - Fortisan
1
6.58
-8.85
-15.43
2
6.55
-8.95
-15.50
3
4.85
8.40
3.55
4
6.60
10.30
3.70
**5
-15.30
21.20
18.25
**6
-13.90
22.80
18.35
**7
-14.30
46.40
30.35
8
6.58
35.85
29.27
**9
-10.90
58.95
34.93
**lc)
_14.33
55.73
35.03
**11
-13.97
43.30
28.63
**12
-17.40
40.10
28.75
**13
-12.97
23.50
18.23
14
4.43
22.46
18.03
15
4.16
12.20
8.04
16
3.04
11.26
8.12
17
5.06
3.80
-1.26
18
5.67
4.05
-1.62
9.60 -5.83 -40.76 -43.41
8.85 -6.65 -41.68 -44.33
6.23 9.78 -25.15 -27.20
5.81 9.51 -25.52 -27.57
3.35 21.60 -13.33 -14.74
2.05 20.40 -14.63 -16.04
.85 31.10 -3.83 -4.55
.40 29.67 -5.36 -6.08
0 34.93
o 35.03
..65 29.28
.80 29.55
-2.55 15.68
.05 18.08
-5.85 2.19
-3.25 4.87
-10.00 -11.26
-10.20 -11.82
*Reference page e9 for explanation of column headings.
**These scales were half-scale inverted.
0
-5.65
-4.93
-5.48
-4.76
-19.25
-17.84
-16.95
-15.54
-32.74
-30.69
-30.16
-28.11
-46.19
-43.54
-46.85
-44.20
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GOODAEAR
AIRCRAFT
GER 8499
Table No, 26
Wing Aspect Ratio = 8.15
15% of Maximum Symmetrical Load
at 60 PSI Internal Pressure
Cover Ply Material - Fortisan
0 * 0* 0* Ca 0 *
1 -6.53
2 -5.63
3 5.4
4 6.39
5 -15.00
6 -.14.33
7 ....13.80
8 -6.50
9 - 9,60
10 -13:98
11 -12.62
12 -17.52
13 -11.92
14 4.33
15 4.82
16 3.70
17 8.80
18 6.18
3.15
-9.68
-6.90
-2.78
25.88
34.82
3.75
-9.38
-6.20
-3.18
26.27
35.21
6.90
+1.50
-4.70
+6.20
16.90
23.80
8.15
+1.76
-3.65
+5.41
17.68
24.58
8.50
+11.75
-2.05
+13.80
9.30
14.07
9.67
+12.00
-1.8
+13.80
9.29
14.06
25.92
+19,86
-1.45
21.31
1.79
4.21
14.40
+20.90
-.8
+21.70
1.39
3.81
36.6
+23.10
0
23.10
0
0
32:20
23.09
0
23.09
0
0
21.35
+16.98
+2.45
+14.53
8.57
6.15
17.46
+17.49
+ .85
+16.64
6.45
4.03
11.15
+11.53
+7.70
+ 3.83
19.27
14.50
16.05
+11.72
+4.85
+ 6.87
16.22
11.45
11.40
+ 6.58
+15.30
- 8.72
31.82
24,92
10.60
+ 6.84
+12.95
- 6.11
29.20
22.30
10.80
+ 2.00
+22.90
+22.90
44.00
35.06
8.30
+ 2.12
+22.95
-20.83
43.92
34.98
*Reference page 55 for explanation of column headings,
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GOOD/EAR
AIRCRAFT
GER 8499
Table No. 27
Wing Aspect Ratio = 8.15
20% of Unsymmetrical Load
at 40 PSI Internal Pressure
Cover Ply Material - Fortisan
* *
1
6.32
9.12
2
6.26
9.05
3
5.37
12.64
4
7.06
13.82
o14,5
-14.00
+8.20
**6
-12.96
+9.65
**7
-12.95
+15.15
8
6.94
20.61
**9
-11.68
+19.51
**10
-16.20
+15.57
**11
-12.88
+13.40
**12
-17.00
+ 9.85
**13
-10.43
+ 6.50
14
5.36
14.02
15
7.19
10.83
16
5.97
9.76
17
10.27
9.12
18
10.80
9.85
0* 0*
2.80 9.60
2.77 8.85
7.27 6.23
6.76 5.81
11.10 3.35
11.30 2.05
14.05 .85
13.67 .40
15.60 0
15.80 0
13.14 -.65
13.42 +.80
8.46 -.2.55
8.66 + .05
3.64 -5.85
3.79 -3.25
1.15 -10.00
.95 -10.20
*
11.40
-4.20
11.62
13.50
-2.10
12.57
-3.23
14.45
-1.15
13.35
-2.45
14.90
- .70
14.07
-1.73
15.60
0
15.80
0
12.49
-3.11
14.22
-1.58
5.91
-909
8.71
-7.09
-2.21
-17.81
.54
-15.26
-8.85
-24.45
-9.25
-25.05
*Reference page 61 for explanation of column headings.
**These scales were half-scale and inverted.
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GOODATAR
AIRCRAFT
GER 8499
Table No, 748
Wing Aspect Ratio = 8.15
40% of Unsymmetrical Load
at 40 PSI Internal Pressure
Cover Ply Material - Fortisan
* 0 * * 0 * * 0 *
1 6.14 5.12 -1.02 9.60 8.58 -20.91
2 6.08 4.97 -1.11 8.85 7.74 -22.23
3 4.89
4 6.58
**5
..14.82
**6
_13.78
**7
-13.00
8
6.91
**9
-11.18
**10
-15.50
**11
-12.85
**12
-16.98
**13
-12.15
14
4,54
15
+4.97
16
+3.68
17
+6.28
18
+6.77
14.20
9.31
16.15
9.57
+22.00
18.41
+24.00
18.64
+39.30
26.15
33.48
26.57
+47.80
29.49
+44.44
2997
+29.40
21.12
+28.20
22.59
+ .85
6.50
12.20
7.66
-4.05
-9.02
_4.30
-7.98
-17.10
-23.38
-17.60
-24.37
6.23 15.54 -13.95
5.81 15.38 _14.59
3.35 21.76 - 7.73
2.05 20.69 - 9.28
.85 27.00 _ 2.49
.40 26.97 _ 3.00
0 29.49 0
o 29.97 o
-.65 20.47 - 9.02
.80 23.39 - 6.10
-2.55 3.95 -25.54
.05 7.71 -22.26
-5.85 -14.87 -44.36
-3.25 -11.23 -41.20
-10.00 -33.38 _62.87
-10.20 -34,57 -64.54
*Reference page 61 for explanation of column headings.
**These scales were half-scale and inverted.
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8
6.85
*49
-11.06
**10
-15.38
**11
-12.76
**12
-16.86
**13
-12.06
14
4,56
15
4.95
16
3.66
17
6.27
18
6.77
SECRET
GOOD/EAR
AIRCRAFT
GER 8499
Table No. 29
Wing Aspect Ratio = 8.15
20% of Unsymmetrical Load
at 60 PSI Internal Pressure
Cover Ply Material - Fortisan
000*
1 6.20 23.93
2 6,10 24.73
3 4,85 25.88
4 6.55 28.68
*45 _14.76 34.70
**6 -13.62 37.04
**7 -12.86 40.00
34.08
44.00
35.22
36.90
30.80
28.80
22.79
22.28
19.39
20.30
21.10
17.73
6.90
24.63
18.63
6.20
24.83
21.03
4.70
25.73
22.13
3.65
25.78
24.73
2.05
26.78
25.33
1.80
27.13
26.43
1.45
27.88
27.23
.80
28.03
27.53
o
27.53,
27.53
o
27.53
24.83
-2.45
22.38
23.83
-.85
22.98
20.43
-7.70
12.73
18.23
-4.88
13.38
17.33
-15.30
2.03
15.73
-12.95
2.78
14.73
-22.90
_8.17
14.33
_22.95
-8.62
*Reference page 61. for explanation of column headings.
**These scales were halfscale and inverted.
0 *
-2.90
-2.70
-1.80
_1.75
-.75
-.40
+.35
+.50
o
o
-4.55
-J.14.80
-14.15
4-25.50
_24.75
-35.70
-36.15
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SECRET
GOOD/EAR
AIRCRAFT
GER 8499
Table No, 30
Wing Aspect Ratio
40% of Unsymmetric
at 60 PSI Internal
Cover 'Ply Material
= 8.15
al Load
Pressure
_ Fortisan
1
6.10
16.30
10.20
6.90
17.10
-12.40
2
6.00
17.00
11.00
6.20
17.20
-12.30
3
4.80
20.80
16.00
4.70
20.70
-8.80
4
6.50
23.70
17.20
3.65
20.85
-8.65
**5
-14.80
28.60
21.70
245
23.75
-5.75
**6
-13.64
32.96
23.30
1.80
25.10
-4.40
**7
-12.90
41.50
27.20
1.45
28.65
-.85
8
6.82
34.92
28.10
.80
28.90
. -.60
**9
-11.10
48.00
29.50
0
29.50
o
**10
-15.40
43.60
29.50
0
29.50
0
**al
-12.80
36.00
24.40
-2.45
21.95
-7.55
**12
-16.90
31.50
23.70
-.85
22.85
-6.65
**13
-12.10
17.90
15.00
-7.70
7.30
-22.20
14
4.52
17.32
12.80
-4.85
7.95
-21.55
15
4.92
10.12
5.20
-15.30
-10010
-39.60
16
3.64
7.34
3.70
-12.95
-9.25
-38.75
17
6,24
1.94
-4.30
-22.90
-27.20
-56.70
18
6.72
1.82
-4.90
-.22.95
-27085
-57.35
*Reference page 61 for explanation of column headings.
**These scales were half-scale and inverted.
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GOODAEAR
AIRCRAFT
GER 8499
Table No. 31
Wing Aspect Ratio = 8.15
15% of Maximum Symmetrical Load
at 20 PSI Internal Pressure
Cover Ply Material - Dacron with Fiberglas
0* 0* (1)* CD* 0 0* CD* 0*
1 8,55
2 8.72
3 7.08
4 6.88
**5 -14.00
**6 -15.02
**7 -14.75
8 6.00
**9 -13.30
**10 -14.74
**11 -15.76
**12 -17.00
**13 -16.32
14 5.83
15 3.80
16 3.53
17 4.81
18 4.56
13.70
5.15
-.70
4.45
+.52
-1.21
13.90
5.18
-.70
4.48
+.55
-1.18
11.92
4.88
-,50
4.38
+.45
-.88
11.77
4.89
-.45
4,44
+.51
-.82
-4.95
4.53
-.10
4.43
+.50
-.42
-5.82
4.60
-.10
4.50
+.57
-.35
-6.40
4.18
+.10
4.28
+.35
-.12
10.30
4.30
+.22
4.52
+.59
+.12
-5.44
3.93
o
3.93
0
0
-6.88
3.93
0
3.93
0
o
-9.30
3.23
+.30
3.53
-.40
+.07
-10.38
3.31
+.10
3.41
-.52
-.05
-11.50
2.41
+.70
3.11
-.82
+.10
8.32
2.49
-.05
2.44
-1.49
-.57
5.28
1.48
+.80
2.22
-1.71
-.38
5.56
1.0
o
2.0
-1.90
-.57
5.80
.99
o
.99
-2.94
-1.21
5.60
1.04
o
1.04
-2.89
-1.16
*Reference page 59 for explanation of column headings.
**These scales were half-scale inverted.
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8
5.71
**9
-11.18
**10
-15.65
**11
-15.62
**12
-17.68
**13
-16.10
14
5.62
15
3.97
16
3.76
17
5.04
18
4.62
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GOOD/EAR
AIRCRAFT
GER 8499
Table No. 32
Wing Aspect Ratio = 8.15
30% of Maximum Symmetrical Load
at 20 PSI Internal Pressure
Cover Ply Material - Dacron with Fiberglas
0 * 0 * * 0* 0* 0* 0 * 0*
1 7.85 14.97 7.12 -.70 6.42 -.10 -2.78
2 8.42 15.86 7.44 -.70 6.74 -.47 -3.15
3 6.64 13.96 7.32 .50 6.82 +.30 -1.77
4 6.96 13.98 7.02 -.45 6.57 -.64 -2.71
**5 -14.05 -.22 6.91 -.10 6.81 +.29 -1.14
**6 -15.50 -.80 7.35 -.10 7.25 +.04 -1.39
**7 -14.72 -1.25 6.74 +.10 6.84 +.32 _.41
13.00 7.29 +.22 7.51 +.30 -.43
+1.85 6.52 0 6.52 0 0
_1.25 7.21 0 7.21 0 0
-4.96 5.33 +.30 5.63 -.89 _.16
-5.72 5.98 +.10 6.08 -1.13 -.40 . .
-8.28 3.41 +.70 4.61 -1.91 -.48
10.10 4.48 -.05 4.43 -2.78 -1.35
6,36 2.39 +.80 3.19 -3.33 -1.26
6.67 2.91 0 2.91 -4.30 -2.23
6.12 1.08 0 1.08 -5.44 -2.76
5.98 1.36 0 1.36 -5.85_ -3.17
*Reference page 59 for explanation of column headings.
**These scales were half-scale inverted.
88
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*4'5
-14.18
4.30
**6
-15.55
-.80
*47
-14.65
+.70
8
5.80
13.50
*49
_10.90
+4.92
*410
-15.05
+.83
11
-15.48
-1.74
**12
-17.48
-3.22
**13
-16.12
-5.20
14
5.62
11.39
15
4.74
8.80
16
3.68
8.00
17
5.12
8.54
18
4.38
7.24
SECInt
400DAVEAR
AIRCRAFT
GER 8499
Table No. 33
Wing Aspect Ratio 8.15
45% of Maximum Symmetrical Load
at 20 PSI Internal Pressure
Cover Ply Material -1)acron with Fiberglas
0 * 0* 0* 0 *
1 7.40 13.84 6.44 -.70 5.74 -2.17 -3.49
2 8.03 14.56 6.52 -.70 5.82 -2.12 -3.44
3 6.68 13.52 6.84 -.50 6.34 -1.57 -2.59
4 6.46 13.36 6.90 -.45 6.45 -1.49 -2.51
7.24 -.10 7.14 -.77 -1.47
7.38 -.10 7.28 -.66 -1.36
7.67 +.10 7.77 -.14 -.50
7.70 +.22 7.92 -.02 -.38
7.91 0 7.91 0 0
7.94 0 7.94 0 0
6.87 +.30 7.17 -.74 -.38
7.13 +.10 7.23 -.71 -.35
5.46 4,70 6.06 -1.85 -1.15
5.77 -.05 5.72 -2.22, -1.52
4.0 +.80 4.86 -3.05 -2.03
4.32 0 4.32 -3.62 -2.60
3.42 0 3.42 -4.49 -3.17
2.86 0 2.86 -5.00 -3.76
*Reference page 59 for explanation of column headings.
**These scales were half-scale inverted.
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GOODALAR
AIRCRAFT
GER 8499
1 7.36
2 7.91
3 6.69
4 6.42
**5 -14.23
**6 -15.40
**7 _14.88
8 5.74
**9 -10.97
**Do -15.0
**11 -15.32
**12 -17.26
**13 -15.90
14 5.70
15 3.66
16 3.62
17 4.93
18 4.48
Table No. 34
Wing Aspect Ratio = 8.15
60% of Maximum Symmetrical Load
at 20 PSI Internal Pressure
Cover Ply Material - Dacron with Fiberglas
13.90
6.54
-.70
5.84
-2.67
-5.37
13.95
6.04
-.70
5.34
-3.19
-5.89
13.90
7.21
-.50
6.71
-1.80
-3.88
13.70
7.28
-.45
6.83
-1.70
-3.78
1.20
7.72
-.10
7.62
-.89
-2.33
.40
7,90
-.10
7.80
_.73
-2.17
1.80
8.34
4.10
8.44
-.07
-.80
1445
8.41
+.22
8.63
+.10
-.63
6.0
8.51
o
8.51
0
o
2.00
8.53
o
8.53
o
o
-1.80
6.76
+.30
7.06
-1.45
-.72
-3.10
7.08
+.10
7.18
-1035
-.62
-6.80
4.55
4.70
5.25
-3.26
-1.82
10.68
4.98
_45
4.93
-3.60
-2.16
6.10
2.44
4.80
3.24
-5.27
-3.19
6.21
2.59
o
2.59
-5.94
-3.86
540
.07
o
.07
-8.44
-5.74
4.81
.33
0
.33
-8.20
-5.50
*Reference page 59 for explanation of column headings.
**These scales were half-scale inverted.
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GOOD/WEAR
AIRCRAFT
GER 8499
Table No. 35
Wing Aspect Ratio = 8.15
40% of Unsymmetrical Load
at 20 PSI Internal Pressure
Cover Ply Material - Dacron with Fiberglas
0* 0* CD*
1 8.62
2 9.23
3 7.43
4 7.33
*45 -13.55
**6 -14.45
*47 -14.60
8
6.05
*49
-10.85
4410
-14.60
*411
-15.12
**12
-16.44
4413
-15.52
14
6.15
15
3.98
16
4.18
17
5.29
18
5.05
22.88
14.26
-.70
23.50
144.27
-.70
21.56
14.13
-.50
21.56
14.23
-.45
14.63
14.09
-.10
13.86
14.15
-.10
13.44
14.02
+.10
20.08
14.03
+.22
17.20
14.02
0
13.52
14.06
0
11.98
13.55
+.30
10.86
13.65
+.10
10.08
12.80
+.70
19.06
12.91
-.50
16.02
12.04
+.80
16.02
12.02
0
16.54
11.25
0
16.28
11.23
0
0*
cn*
13.56 -.46
13.57 -.49
13.63 -.39
13.78 -.28
13.99 -.03
14.05 -.01
14.12 +.10
14.25 +.19
14.02 0
14.06 0
13.58 -.44
13.75 -.31
13.50 -.52
12.86 -1.20
12.84 -1.18
12.02 -2.04
11.25 -2.77
11.23 -2.83
*Reference page 61 for explanation of colummaheadings.
**These scales were half-scale and inverted.
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Goo�"(EAR
AIRCRAFT
GER 8499
0* 0*
1 8.88
2 9.45
3 7.55
4 7.40
"5
-13.65
v1.6
-14.55
**7
-15.18
8
5.72
**9
-11.75
**10
-15.8
"11
-15.66
**12
-17.38
**13
-15,96
14
5.86
15
3.88
16
4.00
17
5.30
18
5.02
Table No, 36
Wing Aspect Ratio = 8,15
80% of Unsymmetrical Load
at 20 PSI Internal Pressure
Cover Ply Material - Dacron with Fiberglas
0*
0*
25,25 16.37 -.70 15.67
25.88 16.43 -.70 15.73 .22
23.52 15.97 -.50 15.47 .23
23.53 16.13 -.45 15.68 .17
17.92 15.79 -.10 15.69 .45
17.20 15.87 -.10 15.77 .26
15.86 15.52 +.10 15.62 .38
21.32 15.60 +.22 15.82 .31
18.72 15.24 0 15.24 0
15.13 15,51 0 15.51 0
11.48 13.57 +.30 13.87 -1.377
10,44 13.91 +.10 14.01 -1.50
6.92 11,44 +.70 12.14 -3.10
17.65 11.79 -.05 11.74 -3:77
12.50 8.62 +.80 9.42 -5.82
13.40 9040 0 9,40 -6.11
12.16 6.86 0 6.86 -8.38
12.02 7.00 0 -7.00 -8.51
*Reference page 61 for explanation of column headings.
**These scales were half-sclae and inverted,
.43
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���11.1M�Milli0.1�1011.1010011.11Mr.1�111101111��������wm�mi
Approved for Release: 2019/04/09 CO2014934
SECRET
GOODAVEAR
AIRCRAFT
GER 8499
Table No. 37
Wing Aspect Ratio = 8.15
100% of Unsymmetrical Load
at 20 PSI Internal Pressure
Cover Ply Material - Dacron with Fiberglas
* * * 0 * 0 * 0 * *
1
8.62
26.66
2
9.15
27.32
3
7.53
24.88
4
7.17
24.80
**5
-13.68
19.58
**6
-15.04
19.00
**7
-15.03
16.84
8
5.69
22,06
**9
-11.60
19.04
**10
-15.87
16.00
**11
-15.80
10.56
**12
-17.42
9.96
**13
-16.25
4.28
14
5.74
16.48
15
3.69
10.94
16
3.84
11.42
11?
5.06
904
18
4.78
9.30
18.04 .7.70 17.34 2.02
18.17 -.70 17.47 1.54
17.35 -.50 16.85 1.53
17.63 -.45 17.18 1.25
16.63 -.10 16.53 1.21
17.02 -.10 16.92 .99
15.94 +.10 16.04 .72
16.37 +.22 16.59 .66
15.32 0 15.32 0
15.93 0 15.93 0
13.18 +.30 13.48
13.69 +.10 13.79 -2.14
10.27 +.70 10.97 -4.35
10.74 -.05 10.69 -5.24
7.25 +.80 8.05 -7.27
7.58 0 7.58 _8.35
4.28 0 4.28 -11.04
4.52 0 4.52 -11.41
*Reference page 61 for explanation of column headings.
**These scales were half-scale and inverted.
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GOOD/EM(
AlFtCRAFT
OER 8499
EXPLANATION OF COLUMN READINGS
COMPARISON DATA, TEST PANEL TO SIMULATED WING
Points where deflections measured, reference Figures 17 and 18.
Measured deflections of test panel.
Twist of specimen in radians, determined by dividing difference of
forward and aft deflection by appropriate distance indicated in either
Figure 17 or 18.
Deflection at 50% chord line of specimen. Determined by averaging
forward and aft deflections.
Non dimensional multiplication factor for converting twist of te6t
specimen to twist of simulated wing. Reference Figures 4 and 5.
Non dimensional multiplication factor for converting bending de-
flection of test specimen to bending deflection of simulated wing.
Reference Figures 4 and 5.
The twist of the simulated wing. Determined as the product of
columns three and five.
The bending deflection of the simulated wing. Determined as the
product of columns four and six.
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1 .15
2 -.30
3
4
5
6
7
8
9
Table No, 38*
Wing Aspedt Ratio = 3.70
100% of Unsymmetrical Load
at 60 PSI Internal Pressure
Cover Ply Material - Fortisan
GOODAVEAR
AIRCRAFT
GER 8499
.164 .475 11j.5 99.0 .186 .0742
.25
.043
. 04
97.5
-.17
.35
.022
. 15
84.5
-.05
.25
.011
. 10
71.0
-.05
97.5 .0419 .039
95.5 .0186 .143
90.0 .0782 .090;
10
11
0
-.80
0
100
100
-.80
71.0
90.0
12
-.80
13
-2.70
0
-2.70
84.5
95.5
14
-2.70
15
-5.15
-.005
-5.20
97.5
97,5
16
-5.25
17
-7.50
- .15
-7.70
113.5
99.0
18
-7.90
*Reference page 94 for explanation of column headings.
0
0 -.72
0 -2.58
-.00487 -5.07
-.17 -7.63
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GOOD/EAR
AIRCRAFT
GER 8499
-1
2 _8.53
3 -5.43
4 -5.67
5 -2,83
6 -2,99
7 -.59
8 -.92
9
'10
11
12
13
14
15
16
17
18
Table No. 39*
Wing Aspect Ratio = 3.70
100% of Maximum Symmetrical Load
at 60 PSI Internal Pressure
Cover Ply-Material - Fortisan
.11 -8.37 113.5 994 .125 -8,29
.024
.009
.013
o
-5.55
97.5
97.5
.0234
-2.91
84.5
95.5
.0076
_ .75
71.0
90.0
.002
o
1.00
1.00
o
-.92
-.0023
- .87
71
90
-.0o16
- .83
-2.92
.0078
-2.99
84.5
95.5
.0066
-3.06
-5.58
:oc(5
-5.61
97.5
97.5
.0063
-5.64
-8.21
.119
-8.36
113.5
99.0
.135
-8.52
*Reference page 94 for explanation of column headings.
-5.41
-2.78
- .67
o
- .78
-2.85
-5.48
_8.28
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GOOD/EAR
AIRCRAFT
GER 8499,
Table No. 40 *
Wing Aspect Ratio = 8.15
60% of Maximum Symmetrical Load
at 20 PSI Internal Pressure
Cover Ply-Material - Dacron with Fiberglas
0 0 0 0 0 0 CD CD
1 -5.37
2 -5.89
3 -3.88
4 -3.78
5 -2.33
6 -2.17
7 - .80
8 -.63
9
10
11
12
13
14
15
16
17
18
.069 -5.63 90.3
-.0125
-3.83
81.0
-.0117
-2.20
74
-0072
- .71
68
82.0
.062
-4.61
82.5
-.0101
-3.16
80.5
-.0086
-1.77
77.5
-.0049
- .55
0
0
..,72
0
-0045
0
- .67
1.00
68
1.00
77.5
0
-.0031
0
- .52
�. ,62
-1.82
.023
-1.99
74
80.5
1017
-1.60
_2.16
-3.19
.086
-3.47
81
82.5
.070
-2.86
-3.86
-5.74
.032
-5.62
90.3
82.0
-.029
-4.61
-5.50
*Reference page 94 for explanation of column headings.
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GOODAEAR
AIRCRAFT
GER 8499
Table No. 41*
Wing Aspect Ratio = 8.15
100% of Unsymmetrical Load
at 20 PSI Internal Pressure
Cover Ply Material - Dacron with Fiberglas
@0 @00000
1 2.02
2 1.54
3 1.53
4 1.25
5 1.21
6 .99
7 .72
8 .66
9
.064 1.78 90.3 82.0 .058 1.46
.035
.016
.0025
0
1.39
81.0
82.5
.028
1.14
1.10
74
80.5
.012
.88
.69
68
77.5
.0017
.53
1.00 1.00 0 0
10
0
11
-1.84
.013
-1.99
68
77.5
.0088
-1.54
12
-2.14
13
-4.35
.06
_4.79
80.5
.004
-3.86
14
15
-7.27
.139
-7.81
814
82.5
.112
-6.44
16
-8.35
17
-11.04
.049
-11.22
90.3
82.0
.044
-9.17
18
-11.41
*Reference page 94 for explanation of column headings.
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GOODAINEAR
AIRCRAFT
GER 81+99
APPENDIX B
TEST RESULTS IN
GRAPHICAL FORM
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GOODATAR
AIRCRAFT
GER 8499
1 1
Figure 20
wing Aspect Ratio = 3.70
Deflections for 20%, 40%, 80% of .11
Maximum Symnatrical Load V
at 20 PSI Internal Pressure
Cover Ply Material - Dacron
111.41T Ji: r1L
11T II 11 1111111 'III" !II iiv, I
1 11 li
t
1111 111111111 1-111YA1111111111 1111i 111111
111114ll 111 lil IIII 1 1 11111
20 IllIlIl II Load IIII
11111101I III 1111111 III
111111101111111 1111110 INIllllIOII1NIIUIIHiII II 111111111111
11111111111111111111111111111 ilii11111111111111111111111 1111 1111111�111
1111111111i111111111111111111 11 1111111111111111111111 III 111111111111111
lir 11111111111011 1 ill"' 1111 I
Ill
111101 I 11 1 iiiip
Ill1 1 ill III
1
60 III IL 111
11111 ��,��� 1111111
'
I. I I
_1;1 I
Ii
iii
Leading
Edge 8
Edge 6
0 -10 0 -10 0 -10 -20
Deflection (8) Inches
100
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70
6o
50
3
20
Span - 10
Inches
0
10
20
30
LO
50
6o
70
, t
Figure 21
Wing Aspect Ratio 3.70
Deflections For 20% 41,0% of
Maximum Symmetrical Load
at 40 PSI Internal Pressure
Cover Ply Material l- Dacron
t
GOODATEACI
AIRCRAFT
GER 8499
I I I
Leading
Edge 6
Edge 6
0 �10 �20 0 �10 �20
Deflection () Inches
4-4 � 1
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1
30
Span
Inches 0
10
30
50
60
j.
70,1 I I� r
SECRET
� �i � �_1� � .1
Figure 22
Wing Aspect Ratio =13.70
Deflections for 80% & 100% of
Maximum Symetrical !Load
at 40 PSI internal Pressvre
Cover Ply Material - Dacron
_
; 1
100(') Load
-10 -20 0 -10
Deflection (6) Inches
-20
(1 INDADYLI
AIRCRAFT
GU 8499
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GOOMOVEAR
AIRCRAFT
GER '499
Span -
Inches
1-111LU-+ h,utPJE:PILLIIP-uh
Figure 23
Wing Aspect Ratio = 3.70
Deflections for 20%, 40%, & 60% of:
Maximum Symmetrical Load
at 60 PSI Internal Pressure
Cover Ply Material Fortisan
.1111 111
dri
11 Ili! pi
��,� ill,��,�.., .11 HER IIIIIIP II1111 111111
111111011111 111111:91111110111111111111111111111111 1111111
111111111 20% Load I
p mm num
60$ Load
immouri umileumuir Him IN
I 1 111011111111111111111111111 I 1111 1111
Leading
M111111111 HI
Edge S
Mill IMIO 1111011111 i Edge 6 IN 11101111 11111
IMP 01111MOMMEMP nuil impel!!! illopm . 1
__ �Trailing 1 mil 1 1
Mir RIMMIMMIMMI Mkillilldi MN ddlilli Mil
11111111 11111111111. .11111111111111 III
1
111111101111111 111111111111111 I 1
i nammenoomoL MIRIMEMIll '
M1111111iliihiMitilli Mg MIRE
.110111111011111
0 -5 0 -5
Deflection (S) Inches
(Note: Deflection Scale 2 Times Span Scale
-5
mffiiU!pto. guoul
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Span �
Inches
SECRET
GOOD/TAR
AIRCRAFT
GER 84-99
E-
40
3
204.,____
o
10
20
50
60
70
F
Figure i14, JUL
Wing Aspect Ratio = 3.70
.7'1 ..�
_.
1:1
Deflections for PO% & 100% of
Maximum Symmetrical Load
at 60 PSI Internal Pressure 1
Cover
Ply
Material
-
Fartisan
1
_....L.,-,
A
- .4
1
-
-14-
i
[
- -
I L
,--F
,
1011
1
I

L
�
q1
11111
111
III
hi
11
I
Ilin
14
RIM
Irk
Load
UO6
100%
Load
i
.i80%
-
, LI
-!i
h
- -11
-
.
1-,ii-
h
-
1
[--,
1
:�-
r .
�
t
1
111
II,
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AIRCRAFT
GER 8499
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Span -
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Maximum Unsymmetrical Load 1J
at 60 PSI Internal Pressure
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Approved for Release: 2019/04/09 CO2014934
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at 60 PEI Internal Pressure
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Approved for Release: 2019/04/09 CO2014934
0
-5
-10
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Approved for Release: 2019/04/09 CO2014934
SECRET
Span -
Inches
140
0
100
80
60
20
20
60
80
100
120
140 _J
Figure 27
Wing Aspect Ratio xt 8.15
Deflections for 15% of 41,
Maximum Symmetrical Load
at 40 PSI Internal Pressure ,t
Cover Ply Material - Partisan
-.1-111171-t 11- :#
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0 -20 -40 -60
Deflection (S) Inches
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AIRCRAFT
GER 8499
SECRET
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107
Approved for Release: 2019/04/09 CO2014934
SECRET
GOOD/STAR
AIRCRAFT
GER 8499
c _OA 1E1: itt
Figure 26,
Wing Aspect Ratio lit 8.15
Deflections for 15% of
Maxim* Symmetrical Load
at 60 PSI Internal Pressure
Cover Ply Material - Fortisan
140
120
100
80
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'wow 20
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0 -20 .40 -60 -80
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SECRET
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Span -
Inches
140
120
100
80
6
20
20
80
100
120
140
_
Figure 29
Wing Aspect Ratio = 3.15
, Deflections for 20% & 40% of
Maximum UnsymIretrical Load
at 40 PSI Internal Pressure
Cover Ply Material - Fortisan-,
, ..
ILI f
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AIRCRAFT
GM 8499
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0 -20 0 -20 -40 -60 -80
Deflection Inches
SECRET
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120
100
80
6o
14-0
20
Span -
Inches
6o
80
SECRET
.1i.
Figure 30
Aspect Ratio r�-.; 6.15
Deflections for 20% & 40% of
14pcimum Un53mmetrical Load
vt 60 PSI :ItIterncl Presauro
Cover Ply Fortisan
I 4 '
100 Lj
r
120
lko
0 -20 -110
GOOD"EALI
AIRCRAFT
GER 8499
0 -zo -40 -60
Deflection ( ) Inches
SECRET
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110
Approved for Release: 2019/04/09 CO2014934
SECRET
GOOD/EAR
AIRCRAFT
GER 8499
Span -
Inches
A:Ltii HI Li . ,11711.1:2.1111111-Itain.
Figure 31
Wing Aspect Ratio gm 8.15
Deflections for 15% & 30% of
Maximum Symmetrical Load
at 20 PSI Internal Pressure
Cover P1,4, Material A. Dacron with Fiberglac
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20
20
80
100
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SECRET
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Span -
Inches
!Figural 32
Wing Aspect Ratio = 8.15
Deflections for 45% &.60% of
Maximum Zymmetrical Load
at 20 PSI Internal Pressure
[Cover Ply Material - Dacron with Fiber
120_
801
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zoL
20
60
80
100iLL,
LL_
120
140
0 -5 0 -5
Deflection () Inches
(Note: Deflection Scale 2 Times Span Scale)
SECRET
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GOODAEAR
AIRCRAFT
GER 8499
112
Approved for Release: 2019/04/09 CO2014934
SECRET
GOOD"EACt
AIRCRAFT
GER 8499
Span -
Inches
140
120
100
80
6
0
/)
80
100
0
140
Fikure 35
Wing Aspect Ratio = 8.15
Deflections for 40%, 80%, & 100% of
I I ,Maximum Unsymmetrical Load
at 20 PSI Internal Pressure
Cover Ply Material - Dacron with Fiberglas
it
I 111111011111 Il 1110P11I 11111 I I! IMMIll
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-ZO
SECRET
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SECRET
GOOD/(AR
AIRCRAFT
GER 8499
Span -
Inches
70
6
20
10
10
20
30
6
Htaill,thilieatalkatitihalhluut
1.1 AveWrillgage
� 1--
Maximum Symmetrical Load
i im he mi.; 1111
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0 -10 -20 -30 -40
Deflection (6) Inches
SECRET
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L14
Approved for Release: 2019/04/09 CO2014934
Span -
Inches
1140
SECRET
GOODAINEAR
AIRCRAFT
GER 8499
� IA i :.[., 1.-.1. :_L" '1 H IALLIIft1-11�LE-11ffilli il
: Figure 35
T1
,
, ^ Wing Arpect Ratio s= 8.15
:... Average Ief1ection for 15% of
111]
11 Symmetrical; Load tri
. ilti ibi II )1:1. 1 .1-tt ir. ,..iiti L 111_
11111
120 r
80
60-
20
0
20
80
100
120
. .
---- 20 PSI Internal Pressure
.Cover Ply Nat'l -
Dacron W/Fiberglas
140 PSI Internal PressureE
Cover Ply Nat'l -
Fortisan
60 PSI Internal Pressure_
Cover Ply Met,v1 -
Fortisan
0 -20 -40 -60 -80
Deflection (S) Inches
SECRET
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�GOOD/VEAL%
Span -
Inches
-L 1 � I
Figure 36
� Wing Aspect Ratio = 8.1$
77 Average Deflection for 40% LI. Maximum Unsymmetrical Load
20 L.4
20
60
80
100
120
140 '
--20 PSI Internal
Pressure
Cover Ply Mat"). -
Dacron W/Fiberglas
40 PSI Internal
Pressure
Cover Ply Mat']. - fl
Fortisan
60 PSI Internal
Pressure
Cover Ply Mat 'l -
Fortisan
H-
0 -20 -40 , -60 -80
Deflections (2.) Inches
AIRCRAFT
+GER 8499
SECnr77
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Approved for Release: 2019/04/09 CO2014934
70
60
50
40
0
0
Span .
Inches 0
10
20
3
60
70
SECRET
tTil7a1-41111[4:111:Lii--I
Figure 37
Wing Aspect Ratio = 3.70
Comparison of Twist and Deflection of Test Panel
.With Simulated Wing for 100% of Symmetrical Load at
20 PSI Internal Pressure
Cover Ply Material - Fortisan
11600DOVEAR
AIRCRAFT
GER 8499
Note: eat Panel Curve
and Simulated Wing Curve
Coincide.
mu 1 Immo 1 I u NE
1 1"'"111911"111111 I
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IN Emu 11 1 1 1
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0 -10 .30 .20 .10 0 -.10 -.20 -.30
Deflections (s)
Inches Radians
Twist (e)
SECRET
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30
20
10
Span
Inches
0
10
20
30
50
6
70
SECRET
GOODACAR
AIRCRAFT
GER 81499
1-77-:tiN I I .1i.1
Figure 38
Wing Aspect Ratio = 3.70
gomparison of Twist and Deflection of Test Panel
tWith Simulated Wing for 100% of Unsymmetrical Load
at 60 PSI Internal Pressure
Cover Ply Material Fortisan
-t+
[I I
11.T1
I
'
TI
4--
Note: Test Panel Curve
and Simulated Wing Curve
Coincide
1-1
1
4,
j 1J -
I _
I
r 1
1
. r
. T-
------Test Panel
--Simulated
Wing
1
,
0 -10
Deflection (s)
Inches
1 -
30 20 10 0 -10
Twist (E')
Radians
-20 -30
Smarr
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Span
Inches
120
100
80
6
40
20
20
LK)
60
80
100
120
140
Figure 39
Wing Aspect Ratio = 8.15
Comparison of Twist and Deflection of Test Panel
with Simulated Wing for 60% of Symmetrical Load 111
at 20 PSI Internal Pressure
GOOD/VEAL%
AIRCRAFT
GER �3499
Cover Ply Material - Dacron with Fiberglas
0 -10
Deflections (6)
Inches
.10 0 -.10
Twist (e)
Radians
SECRET
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GOOD/WAR
AIRCRAFT
Gt,1? 8499
Spah
Inches
140
120
loa
80
20
20
Figure 40
' 1 Wing Aspect Ratio = 8.15
:Comparison of Twist and Deflection of Test Panel ,
iVilth Simulated Wing for 100% of Unsymmetrical Load
i at 20 PSI Internal Pressure 1
i
" I Cover Ply Material - Dacron with Fiberglas
11 III lii L A r I IIII
MIMI 01111111111 111111111 IIII1
1
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mi 1 Elm ammo KM / III I
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ra III i iiiii ill
100
120'
114.0-7
10 -10
Deflection (0
Inches
.20 .10
Twist (a)
Radians
-.10
SECCITT
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sEcirerr
GOODAINEAR
AJRCRAFT
GER 8499
APPENDIX C
PHOTOGRAPHS OF TESTS
SECRET
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GOODAEAR
AIRCRAFT
GER 8499
Photo 1
Zero Reading Position
ding Aspect Ratio = 3.70
100% of Maximum Symmetrical Load
at 40 PSI Internal Pressure
Cover Ply Material - Dacron
SECRET
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SECRET
GOODAEAR
AIRCRAFT
GER 8499
Photo 2
Deflected Reading Position
Wing Aspect Ratio = 3.70
100% of Maximum Symmetrical Load
at 40 PSI Internal Pressure
Cover Ply Material � Dacron
SECRET
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SECRET
GOOD/EAR
AIRCRAFT
GER 8499
Hhoto 3
Deflected Heading Position
'oiing Aspect Ratio = 3.70
100% of Maximum Symmetrical Load
at 40 PSI Internal Pressure
Cover Ply Material � Dacron
SECRET
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SECRET
GOODAEAR
AIRCRAFT
GER 8499
Photo 4
Zero Reading Position
Wing Aspect Ratio = 8.15
15% of Maximum Symmetrical Load
at 40 PSI Interhal Pressure
Cover Ply Material � Fortisan
SECRET
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GOOD/EAR
AIRCRAFT
GER 814-99
Photo 5
Deflected Reading Position
Wing Aspect Ratio = 8.15
15% of Maximum Symmetrical Load
at 40 PSI Internal Pressure
Cover Ply Material � Fortisan
SECRET
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Photo 6
DePlccLed Heading Position
.varlg Aspect Ratio = 8.15
Maximum Symmetrical Load
sL 4P PSI internal Pressure
ri:c)ver Fly Material � Fortisan
GOODAVEAR
AIRCRAFT
uitai 8499
SECRET
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Photo 7
Deflected Reading Position
ding Aspect Ratio = 8.15
20% of Maximum Unsymmetrical Load
at 40 PSI Internal Pressure
Cover Ply Material - Fortisan
GCOODOVEAR
AIRCRAFT
Gigt 8499
101111�.=����1�11=0
SECRET
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Photo 8
Deflected Reading Position
Wing Aspect Ratio L.: 8.15
20% of Maximum Unsymmetrical Load
at 40 PSI Internal Pressure
Cover Fly Material - Fortisan
GOOD/'EAR
AIRCRAFT
(ER 8499
SECRET
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Photo 9
Zero Reading Position
4ing Aspoct Ratio = 8.15
45% of Maximum Symmetrical Load
t 20 PSI internal Pressure
over Ply Material - Dacron and Fibergi
GOODATAR
AIRCRAFT
UER 8499
SECRET
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1130
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SECRET
Photo 10
Defincted Reading Position
'ofing k.spect Ratio = 8.15
45% of Maximum Symmetrical Load
at 20 PSI Internal Pressure
Cover Ply Material � Dacron and Fibergla:',
GOODAEAR
AIRCRAFT
GER 81499
SECRET
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GOODAEAR
AIRCRAFT
tlroli 8499
Alote 11
DiJcLed Heading Position
Wiri Aspect. iito= 8.15
Maximum Symmetrical Load
2U PA Internal Pressure
(;-vor Ply Mn:teri1 - Dacron an(i Fiber,ts
SECRET
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Yhoto 12
,cl!ecteU Readir4r Position
Asuect Ratio 7 b.15
lag of: Maximum Unsymmetrical Deue
aL 20 PL31 internai Fresure
ver Ply Material - Dacron and Fibei Las
GOODAEAR
AIRCRAFT
ER 8499
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GOOD/EAR
AIRCRAFT
GER 8499
Photo 13
Deflected Reading Position
Wing Aspect Ratio = 8.15
100% of Maximum Unsymmetrical Load
at 20 PSI Internal Pressure
Gover Ply Material - Dacron and Fiberlas
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GOODAEAR
AlFtCFtAFT
GER 8499
REFERENCES
1 Pratt, Kermit G.: A Revised Formula for the Calculation of Gust
Loads: NACA Technical Note No. 2964
2 DeOung, John and Harper, Charles W.: Theoretical Symmetric Span
Loading at Subsonic Speeds for Wings Having
Arbitrary Plan Form: NACA Technical
Report No. 921.
3 Toll, Thomas A.: Summary of Lateral-Control Research: NACA
Technical Report No. 868
Flat, J.:
Evaluation of Methods for Determining Spanwise
Lift Distribution; Army Air Forces Technical
Report No. 4952
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