3. BASIC CONCEPT OF HYPERSONIC LIFTING VEHICLES

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP71B00265R000200130015-9
• Release Decision: RIFPUB
• Original Classification: K
• Document Page Count: 34
• Document Creation Date: December 23, 2016
• Document Release Date: November 21, 2013
• Sequence Number: 15
• Publication Date: March 23, 1965
• Content Type: MISC

Declassified and Approved For Release 2013/11/21 : CIA-RDP71600265R000200130015-9
3. BASIC CONCEPTS OF HYPERSONIC LIFTING VEHICLES
A hypersonic glide vehicle achieves range by exchanging its
kinetic energy, plus a small amount of potential energy, for dis-
tance. The kinetic energy is used to overcome the aerodynamic
drag forces enCountered during the course of the flight. Thus
the aeroballistic glide concept differs from the conventional
notion Of gliding flight in that, for the latter case, the main
source of energy is the potential energy, and altitude is ex-
changed for distance rather than velocity.
The derivation of the equation for the aeroballistic glide
range is based on the fundamental principle that the work done
is equal to the change in energy. For a vehicle having some
initial velocity and moving through a resisting medium, the work
accomplished is equal to the resisting force times the distance
covered. Hence, if the resisting force is known and the initial
and final energy levels are specified, the distance maybe deter-
mined. In the case of a glide vehicle the resisting force is.the
drag, and the initial and final energy is determined from the in-
itial and final glide velocities. This neglects a contribution
of potential energy which is small with respect to the kinetic
energy. The differential equation expressing this energy re-
lationship is
Dds = -dE
;
Declassified and Approved For Release 2013/11/21 ICIA-RDP71600265R000200130015-9
Declassified and Approved For Release 2013/11/21 : CIA-RDP71B00265R000200130015-9 ,
where D is the aerodynamic drag, s is the distance along the flight path,'
;
and B is the kinetic energy. Since the flight-path angle is small, the -
*distance along the flight-path, army be assumed to be equal to the
range, It, so that equation (1) becomes
? (2)
where the limits of integration, Bi and Er, are the initial and final
values of kinetie enera.of the missile, respectively.
Since the 'range ip assumed to be accomplished solely due to the
change in kinetic 'energy, KS .:1/2 mre, the differential, AS, in
equation (l)is
. ,
Also the drag, D, .in equation (2) may be expressed as
' F '''JV -el
0)
D (4)
L
. /WM
where 1.43 is the lift-drag ratio of the vehicle .in glide. Now in:
equilibrium flight over anpherical earth, the aerodynamic lift, (1.),
must be equal to the of. the vehicle rat nun the centrifugal relieving
effect, or ,
?
Declassified and Approved For Release 2-013/11/21 : CIA-RDP71B00265R000200130015-9
Declassified and Approved For Release 2013/11/21 : CIA-RDP71B00265R000200130015-9
c
i where L is the lift
g local acceleration of gravity
W the weight
?ro the radius of the earth : 20.9 x 106 feet
Ii the altitude of the missile above the earth
? Substituting equations (3)) (4), and (5) into equation (2), the range
,
equationteces
?
(L/D)dv2
vi I ' 2.13 [2. 8:2ro+h)
(6)
'This may readaybo integrated, if (L/D) is assumed .constant:,
? 2
.1.. Vf
? 17;TIT-
VI2.
g(rorh)
S. (1/2)(L/D)(reh) ln
.1 (7)
? To gain a better insight into the effect of the primaryparampters,
(L/D) and V, on range, the equation may be further sinpified by noting
that the qmantity:V2/erdrh) is less than 1.0 for the region of velocities
,of interest allowing .the logarithm term to be expended in.afteries.:.
.1!?
I
Declassified and Approved For Release 2013/11/21 : CIA-RDP71B00205R000200130015-9 .
Declassified and Approved For Release 2013/11/21 : CIA-RDP71600265R000200130015-9
N
A first-order approximation to the glide range is thus obtained
by neglecting all terms in the series except the first term which
gives
(L/D)
R -
2g (Vi2 - Vf2)
(8)
This simplification amounts to omitting the effects of the earth's
curvature, i.e.., the effects of centrigugal lift. For the longer
ranges, this results in some appreciable conservatism. Now by
assuming the glide is maintained to near zero velocity, i.e., = 0
Vi2
R = 1/2 (LID)
(9)
This shows clearly the sensitivity of glide range to the initial
velocity and lift-drag ratio.
The flight altitude for glide vehicles is shown in figure (1)
as a function of velocity and the parameter W/SCL. These results
are obtained from the relation established by equating the aerody-
namic lift on the missile to the fraction of the weight not sus-
tained by centrifugal forces
2
L = W (1 - V ---)
= CLEt0
2
where Vs is orbital velocity, and from whence the density becomes
(10)
e - 2 W 1
SCL Vs
The fraction of the weight supported by lift is shown as a function
of velocity in figure (2).
Declassified and Approved For Release 2013/11/21 : CIA-RDP711300265R000200130015-9
Declassified and Approved For Release 2013/11/21 : CIA-RDP71600265R000200130015-9
PAGE
" DATE
REVISED
REVISED
"TAIL VAILIMI11 ?
ST. LOUIS 3. MISSOURI
Coottaran
REPORT
MODEL
GLIDE ALTITUDE FOR LIFTING RE-ENTRY VEHICLES
VELOCITY) 1000 FE ET/S ECU PID
F/C7,1
MAC 1084 A UT ZUL ST)
Declassified and Approved For Release 2013/11/21 : CIA-RDP71600265R000200130015-9
Declassified and Approved For Release 2013/11/21 : CIA-RDP71B00265R000-200130015-9
- -------
REVISED
REVISED
urvyptdagn rAGE
ST. LOUIS 3. MISSOURI
REPORT
MODEL
1
11.f 1'1!
RiMilli
IT . 1 ..
11111111 i11 M!BIOII1I
1111 11110611
ivaihw
h;ujm
1111997,18111 11P2
!IH iIMP
!Min Billffitigilly T
HIRMIWPPMENEMI INPIM M91111
EP din
VE'LO_CITY, )000- FEET/SECOND
Declassified and
MAC
m A a7 JUL llt
prouvedForReleasle 2013/11/21: CIA-RDP71600265R000200130015-9
Declassified and Approved For Release 2013/11/21 :CIA-RDP71600265R000200130015-9
el- ?(4, )
/7 Noe
bozo/
HIGH S \/;
PEED DESCENTS Yr] g'
General calculations are complex but a few simplifying assumptions
can yield results that can be used for approximate checking. First by
assuming the gravity gradient, the planet rotation rate, and airplane
bank angle to be zero, the equations of motion are: ..
1- 7/ 351N V
-.. 9
At very high speeds the flight path angled, is very low, and its
rate of change is small, then, Va
= cos e=,* a ? 1=-- = -
and
V L
v dv L 9 ds -9 cl
L
Now, we must somehow relate dV and dh. A variety of assumptions are
ameniable to calculation and it makes little difference which we choose.
Say,
thus
between
Now,
ct. cONSTAN T
K, V2 ebh -(APPROX)
_ civ
Tr) V
look/ 2 oo K 3, 0 0 0
V (illD d
- -1,-) 3 5 9 ( 4G Goo) cly
elh
and then
?/eo
( 2V41)(R? =
g R o
g /
Integrating, we get for small
EARTH RADIUS) ?
v
4Goo0 orsR01/z
v ,/,_ Va. .\
(91.
Declassified and
itliie.,!dk.eiww-a.sarr..,
0E04 NO.i131 fiThii
? -cisfiik
Approved For Release 2013/11/21: CIA-RDP71B00265R000200130015-9
11194.1%."Etrti- ? I! ? '?????? ?-? ? ? ? -
WORK SHEET.
FOrtTP.AN DATA
Wnw SPEPO De.r.c5w2.1.414 72"4/
REQUESTOR
DATE_ PAGE OF Z
IDENTIFICATION ?
58
17
24
35
44
53
62
71
xatiov
1 4.
M(i)
e...5
(t)
9.
etc.
13.
cl_ (1)
22
(4)
.1105
AC7C .
.1131
? 11.56
9 .0784.
17
25
33
41
Ix uv
.12.
NW
4. ? 5
(C)
7-5
arc.
9
Co, al
_ZZ .
(z)
.11.
erc.
24.
47
18.
11.
20.
21
22.3 ?
OW
.0122.
57
.01.05
.007C
.0023
. 0071
. 0011.
.0095t
. 0098
.0163
65
? 0E4
73
81
xx?uov
t.
ma)
4 .
(4
a.
E7C.
9.
CU)
13.
(e)
16.
arc.
22.3
/8.413S _
87
1.87
1.e,
2.045
2.25
2. L6
77
105
113
X XA/ V
2.
Ha)
0.
a)
22.
arc.
1
Pm (I)
(z)
sic.
121.
121
- /37
145
xi.svx
V(15
(z)
cc.
h(1.1
(z)
e7C :
153
.
MAC 2G Declassified and Approved For Release 2013/11/21 : CIA-RDP71600265R000200130015-9
-
44,
Declassified and Approved For Release 2013/11/21 :
CIA-RDP71 B00265R000200130015-9
Arrucu tvirdricivimik-b
? WORK SHEET?
FoRTRAN DATA
DECK No. TITLE
REQUESTOR
DATE
IDENTIFICATION
PAGE.
17
2e,
35
40
53
CE.
'7/
14,1
it,
177
2182#.
No
205966.
_fro
106 .
335.
10.
A V
50a.
Vat:0
75.5 0 .
G to
251(54 .
1.1
85
Stu
1075.
TEST
0.
CONF76
2#&3
Vs
21)500.
[
,
4AC2 Declassified and Approved For Release 2013/11/21 : CIA-RDP71600265R000200130015-9
?
Declassified and Approved For Release 2013/11/21 : CIA-RDP71600265R000200130015-9
0
HIGH SPEED DESCENDING TURN
ALT.
FT.
MACH
NO.
VEL.
FPS
Mu
DEG.
205700.
21.47
21824.
105.98
203672.
21.03
21500.
104.58
200776.
20.37
21000.
102.73
97975.
19.73
20500.
101.17
95242.
19.11
20000.
99.87
92557.
18.50
19500.
98.82
89914.
17.90
19000.
98.00
87276.
17.31
18500.
97.43
84632.
16.72
18000.
97.09
81997.
16.15
17500.
97.02
79346.
15.59
17000.
97.21
76668.
15.03
16500.
97.68
73954.
14.47
16000.
98.45
71488.
14.02
15500.
99.53
69051.
13.56
15000.
100.93
66593.
13.11
14500.
102.66
63925.
12.66
14000.
104.72
61161.
12.21
13500.
107.11
58354.
11.76
13000.
109.80
55499.
11.30
12500.
112.76
52651.
10.88
12000.
115.91
49943.
10.47
11500.
119.16
47189.
10.06
11000.
122.43
44384.
9.65
10500.
125.59
41517.
9.23
10000.
128.55
38546.
8.82
9500.
131.22
35449.
8.40
9000.
133.54
32260.
7.97
8500.
135.46
28967.
7.55
8000.
136.97
25900.
7.16
7550.
137.99
'CONFIG = 2460.3
Hi?hteie 4 noid CL
0,01
LAMBDA RANGE TIME PSI PHI
DEG. NAM SEC. DEG. DEG.
9.99
0.0
0.0
334.93
45.00
13.15
206.5
57.9
336.39
45.00
17.79
505.3
143.3
338.67
45.00
22.15
781.7
224.3
341.04
45.00
26.25
1038.7
301.4
343.53
45.00
30.13
1278.2
375.1
346.17
45.00
33.79
1502.2
445.8
348.94
45.00
37.24
1711.8
513.7
351.92
45.00
40.49
1907.9
579.0
355.19
45.00
43.55
2091.9
642.0
358.72
45.00
46.42
2264.6
702.8
2.56
45.00
49.12
2426.6
761.6
6.72
45.00
51.64
2578.5
818.4
11.24
45.00
53.99
2721.0
873.3
16.14
45.00
56.17
2854.5
926.5
21.46
45.00
58.16
2979.8
978.1
27.22
45.00
59.96
3097.6
1028.3
33.45
45.00
61.57
3208.4
1077.3
40.17
45.00
62.97
3312.8
1125.2
47.40
45.00
64.16
3410.9
1171.9
55.10
45.00
65.13
3503.1
1217.7
63.24
45.00
65.87
3589.6
1262.4
71.75
45.00
66.39
3670.7
1306.2
80.58
45.00
66.70
3746.8
1349.2
89.65
45.00
66.82
3818.1
1391.5
98.88
45.00
66.75
3884.7
1433.0
108.23
45.00
66.53
3946.7
1473.7
117.63
45.00
66.19
4004.2
1513.7
127.08
45.00
65.75
4057.5
1552.9
136.60
45.00
65.28
4101.8
1587.5
145.25
45.00
Declassified and Approved For Release 2013/11/21 ICIA-RDP71600265R000200130015-9
16
? /
Declassified and Approved For Release 2013/11/21 : CIA-RDP71B00265R000200130015-9
?
WIND TUNNEL RESULTS TO DATE
HYPERSOAIIC (M=14s TO 22)
? VALIDATES HYPERSONIC LiD
PO YSONIC (M=.5
VALIDATES SUPERSOA/IC go
SUBSONIC Qo Low; WE FAIRINGS ./Nce64sE 1/P To. 7.5%
? ELEVATORS AMPLE FOR LONGITuDiNAZ CONTROL AI GLIDE
? TIP EYTENS/oNS INCREASE Zia AND LONGITUDINAL STABIL/TY
?TIP AILERONS PRovioe INcRE.4sEd ROLL aiNreoc . .
? TOED-IN ARRAAmememr OF VERTICAL TAILS IMPROVES DARECT/ONAL STA8/4/TY
? AMPLE Remote POWER AVAILABLE
?? NEUTRAL Po/Air CONSTANT W/TH 44.401 .NUMBER
????? _
? I
LOW SPEED (M=.24)
? DATA AGREES W/771 PoLYsoNIC
? BASE FAIR/Nd 4 VERTICAL TAIL ARRANGEMENT PROVIDES seLp-TRIA4
? LAID PLATE EFFECT OF VERTICALS PAYS FOR THE. IR DRAG
-
? 6000 LATERAL-DIRECTIONAL STABILITY e CONTROL
a
?
_ _ ? .. .?
Declassified and Approved For Release 2013/11/21 : CIA-RDP71B00265R000200130015-6 -
Declassified and Approved For Release 2013/11/21 : CIA-RDP71106265R0002061-50015-9
0 I/Y PEP. SON/C ii2pw.sez iilikWifft
POLYSON/C TUNNEL
0 LOW SPEED TUNNEL.
0/216/NAt ?31/MATE..
D.474 C011'IZECTED 7V FULL SCALE
Ca.V. 0 / 7/01..15
------ Declassified and Approved For Release 2013/11/21 : CIA-RDP71600265R000200130015-9
,
Declassified and Approved For Release 2013/11/21 : CIA-RDP71600265R000200130015-9
? k_l
Arecer..
e:DO
COMPARISON OF
ESTNIATED AND
FLIGHT TEST DRAG
Mt:15 -18
? ASV -3
o ASV -1
THEORETICAL ESTIMATE
.2 .3 A
Declassified and Approved For Release 2013/11/21 : CIA-RDP71600265R000200130015-9
? 210
Declassified and Approved For Release 2013/11/21 : CIA-RDP711300265-R000200130015-9
1/3 vs, ANGLE of: A 7714 CK
3
2 -
I A
0 E3
0
MAC HYPER VE. L 0 C / 7 Y" by/ROL . SE 7-61.,VALE
M /4
- - - 0 BASIC BODY
A COMPL 741: 140D5L
LI CON/ L Ere ODEL,
ELEfrOA/ 5 Air -10?
I WES A RE EST/MATES
FOR PV/M0 TO/IA/EL.
MODEL AT 712.5
COA/D17/0/V5
5. o /5 20
i1/t/6Le OF ATrAcK DE-6.
Declassified and Approved For Release 2013/11/21 : CIA-RDP71600265R000200130015-9
tr* .
Declassified and Approved For Release 2013/11/21 : CIA-RDP71600265R000200130015-9
A/14%.
2
rrri
r I 6,-*r
8.0..(iI pm. ccw4 p
0 TAILS OFF
0 TAILS ON
Pv