to - dticthe base drag on a missile with thrust is generally greatest at low thrust levels and is...
TRANSCRIPT
UNCLASSIFIED
AD NUMBER
AD871913
NEW LIMITATION CHANGE
TOApproved for public release, distributionunlimited
FROMDistribution authorized to U.S. Gov't.agencies and their contractors;Administrative/Operational Use; MAY 1970.Other requests shall be referred to ArmyMissile Command, Redstone Arsenal, AL.
AUTHORITY
USAMC ltr, 15 Nov 1972
THIS PAGE IS UNCLASSIFIED
REPORT NO. RD-TR-70-1 .
O0 INVESTIGATION OF THE EFFECT OF LOW THRUST LEVELSON THE BASE PRESSURE OF A CYLINDRICAL BODY
AT SUPERSONIC SPEEDS
by
T. A. MartinC. E. Brazzel
JMay 1970
-m
S ""This document is subject to special export controls____ and each transmittal to foreign governments or foreign
nationals may be made only with prior approval of thisCommand, ATTN: AMSMI-RD.
R fedston e Arsenal, Alabamn-a
DEOC
~/--
M061 COMMAN
7 May 1970 Report No. RD-TR-70-11
INVESTIGATION OF THE EFFECT OF LOW THRUST LEVELSON THE BASE PRESSURE OF A CYLINDRICAL BODY
AT SUPERSONIC SPEEDS
by
T. A. MartinC. E. Brazzel
DA Project No. IM262301A206AMC Management Structure Code No. 522 1. 11. 148
This document is subject to special export controlsand each transmittal to foreign governments or foreignnationals may be made only with prior approval of thisCommand, ATTN: AMSMI-RD.
Advanced Systems LaboratoryResearch and Engineering Directorate
U. S. Army Missile CommandRedstone Arseral, Alabama 35809
Abstract
Results of supersonic wind tunnel tests are presented which show theeffects of varying nozzle geometry, location, and supply pressure on the basepressure of a cylindrical body at zero angle of attack. The purpose of the testswas to investigate the parametric influences in the regions where base pressureis near a minimum, which occurs in the lower range of thrust levels. Abibliography of related experimental results is also included.
ii
Contents
Page
1. Introduction .......................................... 12. Apparatus........................................ 13. Presentation of Data .................................... 2
Bibliography ............................................. 33
Appendix. Tabulated Test Results ............................. 35
I lustrations
Table Page
* I Nozzle Configuration Variables ........................ 3A-I Index to Tabulated Data ............................. 36
A-II Nozzle Position Data ............................... 38A-III Reynolds Number Data .............................. 39
Figure
1 Model Detail .................................. 52 Base Pressure for Open Versus Closed Base Configurations . . 103 Reynolds Number Effect on Base Pressure .............. .114 Effect of Jet Mach Number on Base Pressure, Constant
Throat Diameter .................................. 125 Effect of Jet Mach Number on Base Pressure, Contoured
Nozzles, Constant Exit Diameter ...................... 146 Effect of Jet Mach Number on Base Pressure, Conical
Nozzles, Constant Exit Diameter ...................... 167 Effect of Nozzle Angle on Base Pressure, Exit Mach
Number = 1.78 ................................ 178 Effect of Nozzle Angle on Base Pressure, Exit Mach
Number = 2.20 ................................... 189 Effect of Nozzle Angle on Base Pressure, Exit Mach
Number = 2.70 ................................... 1910 Effect of Nozzle Angle on Base Pressure, Exit Mach
Number = 3.20 ................................ 2011 Effect of Nozzle Diameter on Base Pressure, Exit Mach
Num ber = 1.00 ................................ 21
111ii
Illustrations (Concluded)
Figure Page
12 Effect of Nozzle Diameter on Base Pressure, Exit MachNumber = 1. 78, Contoured Nozzles ..................... 22
13 Effect of Nozzle Diameter on Base Pressure, Exit MachNumber = 1. 78, Conical Nozzles .................... 23
14 Effect of Nozzle Diameter on Base Pressure, Exit MachNumber = 2.70, Contoured Nozzles .................. 24
15 Effect of Nozzle Diameter on Base Pressure, Exit MachNumber = 2. 70, Conical Nozzles ................... 95
16 Effect of Nozzle Diameter on Base Pressure, Exit MachNumber = 3.20 ............................... 26
17 Effect of Nozzle Position on Base Pressure, Nozzle-BaseRatio = 0.10, Mach Number = 2.50 ..................... 27
18 Effect of Nozzle Position on Base Pressure, Nozzle-BaseRatio = 0.20 . ................................ 28
19 Effect of Nozzle Position on Base Pressure, Nozzle-BaseRatio = 0.30, Mach Number = 2.50 ................. 30
' iv
I. Introduction
The base drag on a missile with thrust is generally greatest at lowthrust levels and is significantly influenced by the various rocket nozzlegeometric parameters. For clarifying the influences of the nozzle geometricparameters, a series of supersonic wind tunnel tests has been conducted with acylindrical body by using cold, dry air to simulate the rocket exhaust. Nozzleparameters varied were diameter, exparsion ratio and expansion angle,longitudinal position, and thrust level.
The basic results of the tests (base pressure variation with nozzlechamber pressure) are presented in plotted form without detailed analysis, butthey are arranged to illustrate major parametric influences. These resultsare repeated in tabular form, and additional -nozzle flow parameters and testcondition information are shown in the appendix.
2. Apparatus
The model was mounted to the tunnel topwall and aligned with thetunnel flow by means of a fixed swept strut which also provided routing of theinstrumentation lines and cold air supply used to simulate the exhaust flow.The external shape of the model was defined by a 4-caliber tangent-ogive noseplus a cylindrical body which w-is 2 calibers long. Details of the model areshown in Figure 1.
Two types of base co-,figurations were used during these tests. Onemodel configuration, designated as the "open base" configuration, contained anactive nozzle mounted concentrically in a larger inactive nozzle. This configu-ration presented considerable base area which was not adjacent to the regionwhere the exhaust was exiting from the model. Also, this configuration wasconstructed so that the exit plane of the active nozzle was located at positionsother than the plane of the model base. This configuration was made by com-bining the nozzles (Figure 1b) and the "open base" body (Figure la).
The model configurations designated as "closed base" were made byinstalling the nozzles, including sonic (Figure lc), conical supersonic(Figure 1d), and contoured supersonic (Figure le) into the body identified inFigure la as the "closed base" body.
Tunnel No. 1 of the Ballistic Research Laboratories is a continuous flow,supersonic wind tunnel capable of operating over the Mach number range of
1
1.20 to 5.0. The test section dimensions are 13 by 15 inches. The minimumtest Mach number for this model in this facility is 2. 5. Complete details ofthis facility are given by Baughman.'
The estimated range of inaccuracy of all data presented herein is asfollows:
Mach number, ±0. 008Local model pressure, ± 0.100 psiAir supply pressure,
0 to 15 psi range +0.030 psi0 to 100 psi range ± 0.200 psi0 to 300 psi range ± 0.600 psi
3. Presentation of Data
The information presented here consists of:
a) Justification fer direct comparison between results obtainedwith open and closed base configurations
b) Observations on the insignificant influence of Reynolds numberover the test Reynolds number range
c) Plotted basic results arranged to illustrate major parametericinfluences
d) Tabulated results.
A detailed listing of the test condition, test configurations, basepressure, and base pressure coefficient variation with nozzle Lhamber pressure,thrust coefficient (CT), and momentum flux ratio (RMF) is presented in theappendix. The values of CT and RMF have been calculated by using measuredvalues, nozzle physical dimensions, and one-dimensional flow relationships.An index to the tabulated data and symbol notation as used in this tabulationare also shown in the appendix.
Two cylindrical body configurations were tested: a closed base configu-ration and an open base configuration, which simulated an inactive large boost
IaBaughman, L. E. , and Kochendorfer, F. D., "Jet Effects on Base
Pressures of Conica! AIL bodies at Mach 1.91 and 3.12," NAGA RM E57E06,.\ igust 1957
Ip9
f I nozzle surrounding an active small sustainer nozzle (Figure la). A comparisonof results from each of the bodies with identical nozzles is shown in Figure 2.This comparison indicates that effects due to base configuration difference arevery slight. On the basis of this comparison, no further reference to the basedifference will be made. Excellent repeatability of data 2cquired in separatetest entries is also shown in Figure 2.
A group of nozzles were tested at a Reynolds number lower than thenominal value to extend the range of thrust level. The results are presentedin Figure 5 together with results obtained at the nominal Reynolds number. Inthese results there is a slight but consistent shift in the base pressure ratio atcomparable chamber press.re ratios, although different chamber pressureswere used to produce the comparable ones. To investigate this shift in basepressure, further testing was conducted both over a greater Reynolds numberrange and without the standard boundary layer transition strip on the nose.These data, presented in Figure 3, show no consistent trends with Reynoldsnumber over the range in question (RN 0. 20 to 0. 50 million per inch). On the
NJ
basis of this observation, it is felt that the shift is due to data acquisition errorsand is not a Reynolds number effect.
The basic results from the test are pre~ented in Figures 4 through 19.The nozzle configuration variable for each group of data is shown in Table I.
TABLE I. NOZZLE CONFIGURATION VARIABLES
Configuration Configuration FigureVariable Constants No.
Nozzle Mach 2,/DB = 0.141, 0. = 0 deg 4No. o.=0. = 0 deg, D /DB= 0.20 5
0.= 20deg, D./D B = 0.20 6
Nozzle Expansion M. = 1.78, D./D B = 0.20 73 j/BAngle M. = 2.20, D j/DB = 0.20 8
M = 2.70, D./ DB 0.20 9
M. = 3.20, D/DB =0.20 10
0' 3
TABLE I. NOZZLE CONFIGURATION VART'iBLES (Concluded)
Configuration Configuration FigureVariable Constants No.
Nozzle Exit M. = 1.0, 0. = 0 11Diameter I I
M = 1.78, 0.= 0 12
M. = 1.78, 0. = 20 133 3
M.= 2.70, 0.= 0 14
M. = 2.70, 0. = 20 deg 153 3
M. = 3.20, 0. = 0 deg 16
Nozzle Exit Nozzle, D /DB= 0.1 17Position Nozzle, D DB = 0.2 18
Nozze, j/D =021Nozzle, D. DB= 0.3 19
The symbols used in these figures are identified in the following list,while those used with the tabulated data are given in the preface of that section.
DB Reference diameter of model
D. Diameter of nozzle at exit plane3
M. Yoz:le design Mach number3Mo Fr ,e stream Mach nun :.,er
PC Jet stagnation pressure
PB Mean base pressure
P"' Free stream static pressure
RN Reynolds number per inch
X Location of nozzle exit plane relative to model base, negativenrearward
0. Half-angle divergence of nozzlesJ
I
- - = = -
Z .. . . - --
U . -
Q r
"I - I-_2 f= I-.iT--
-| =| U.j
LV Li
0
000
U6U
IC) 0C4
o o o
I I I8 I I
LO I _ j
I D'-d Nc~~
CLOSED BASE SONIC NOZZLE
Iii.706 j
/Io --'. -i-"C
M j 1.0 1.0 1.0
Dj/DB 0.100 0.140 0.200
Dj 0.250 0.352 0.500C 0.010 0.010 0.010E 0.404 0.302 0.191
(c) SONIC NOZZLES
FIGURE 1. MODEL DETAIL (Continued)
'7
N1
09 1 80 0
C4 C-
8
N C4
OD 8!0%I- A --
- - -- I-- ---- --Vx
.706 iT + j
C
ZLOSED BASECONTOURED NOZZLES
M! 1.78 1.78 2.20 2.70 2.70 3.20 320- 0 0 0 0 0 0 0
Dj/Dg .168 .200 .200 .200 .252 .200 .320
Dt .352 .420 .352 .280 .352 .220 .362Dj .420 .500 .500 .500 .629 .500 .800
C .591 .703 .909 1.096 1.382 1.249 1.996
(e) CONTOURED NOZZLES
FIGURE 1. MODEL DETAIL (Concluded)
9
ILLU (A-w C 0
o Lu z
a. -ig0 owXI-
U ZIU
4A-w*
z 0
06 z
0
0
r4
10\
PC / POO0NO FLOW
.4
.3
0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8R Nx 10-/n.
aSONIC NOZZLE
0.6 - - - - - - ______
0._ ____ ONO FLOW,
0 1800.4 SOLID SYMBOLS - NO GRIT
8
.3
2.70 0 0.25
1 1 10 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.9
R N X 10'/in.
b. SUPERSONIC NOZZLE
FIGURE 3. REYNOLDS NUMBER EFFECT ON BASE PRESSURE
0
o J
4t C.
is cc 0
- - - -m
~uBP4
oP
d- /'Id
12r1
0
w o
4ka
4 -
-o
400
0.E-4CLr
WP4
a 113
- " - . -~ n' - n n 0 '
sagasm
0 cc A
-- N
cocoa ---- ~ i
o 0
. -°m d / me
a~ z
- - 4.
0 6D II0z
LA 0
0; a
Wd~ /O
14
-.
ii 0
a Z
- a '0
ZO FA
&n J0 0
- --- w 8
0~ z
zA
II 4.54
o E-4
-E-
z* L;
0. * . _
ol'
15
0.30
0.20.2
0 20 40 0 100 120 140 10 IO 20020
2 .0 20 0.200. .20 20 0.20
V 3.0 20 0.20
0.3Apl
0.1
0 20 40 60 80 100 120 140 160 180 200 20PC / W 0
a . N 2 .0
0.6 m j/ DFIGURE ~ ~ ~ ~ ~ ~~10 0. EFETO0.E2AH0MRO AE RSUE
CONICAL~~.7 NOZLS CO0AN.XI2IAEE
162
0. 0 D./D
2.20 20 0.202.70 20 0.20
0. -- -- 2.20 20 0.20OA -n'!73.20 20 0.20
0.2
0.2
0. - - p
0 20 40 60 80 l00 120 140 160 180 200 240
Pc /PmDa. Mo=2.5
0.6 ___ D~0
0.5 - 1.78 20 0.0 02.20 20 0.20
*2.70 20 0.20 '*3.20 20 0.20
&S 0.4 0. 3.80 20 0.20
0.3 A
0 20 40 60 80 100 120 140 160 180 200 220PC /Poo
bo MN0 = 3.0
FIGURE 6. EFFECT OF .JET MACH NUMBER ON BASE PRESSURE,CONICAL NOZZLES, CONSTANT EXIT DIAMETER
16
2.0 0 0.20g. 2.20 20 0.20
a40.3
0.2
0.1
0 20 40 60 80 100 120 140 160 1S0
pc/pwas N z 2.5
9 2.20 0 0.200. 22020 0.20
0.4 -
.2
0.1-- - - - - - - - - - - - - - - - - - - - - -
0 40 80 120 160 200 240 230 300 320
pc/p.b. N 00=3,0
FIGURE 8. EFFECT OF NOZZLE ANGLE ON BASE PRESSURE,EXIT MACH NUMBER = 2.20
18
2.1 0 0 .20 2.70 10 0.2
02.70 05 0.20
40 I*2.70 20 0.200.4
IjI
0.1 - -
0 20 40 60 80 100 120 140 160 160
a., 2.S
S2.70 0 0.20W2.70 1O 020
0. - - - 2,70 1S 0.20*2.70 20 0.20
0.2
0.1
0 40 80 120 160 200 240 280 320 360
b. MN0 3.0
FIGURE 9. EFFECT OF NOZZLE ANGLE ON BASE PRESSURE,EXIT MACH NUMBER = 2.70
1
3.20 0.20o.5 - - - -3.20 20 0.20
* o .4 -- - - - - -
0.2
0.1
0 20 40 60 80 100 120 140 160 180
PC /Pwa. M "2.5
0.6 -- M- ej Dj/ Ds3.20 0 0.20
o. 3.20 200.20
0.4
0,2
0.I
0 40 80 120 160 200 240 280 320 360Pc/ Po
b. M' = 3.0
FIGURE 10. EFFECT OF NOZZLE ANGLE ON BASE PRESSURE,
EXIT MACH NUMBER = 3.20
20
0.8.
11 0.361
0.2
f0.
10 20 40 60 80 100 120 140 160 180
PC /PooNM do2.S
0.6------------------ m DI/De
Q.0 0 0.100.5 -- - -. 0 0 0.14
;;; 9 .0 0 0.20
0.2 -
0.1I0 40 0 12 160200 240 280 320 360 400 440
FIGURE 11. EFFECT OF NOZZLE DIAMETER ON BASE PRESSURE,EXIT MACH NUMBER =1. 00
21
0. 1.7 0 Gel"
0.2
0.2 - -e
0 20 40 60 30 100 120 140 160 160
PC /PoS
0.5 -
,-.%
060.2
0.1 __
0 40 so 120 160 200 240 260
PC /Poo
be N =3.0
FIGURE 12. EFFECT OF NOZZLE DIAMETER ON BASE PRESSURE,EXIT MACH NUMBER = 1. 78, CONTOURED NOZZLES
22
Qi1.78 20 0.10o.s 1.7 20 0.20
0 178 20 0.30
0.4
0.1
0 20 40 60 30 100 120 140 160 180
PC/ Poea. N 2,5
1;.78 20 0.10I , .78 20 0.20
0.5- .78 20 0.30
.3
0 40 80 120 160 200 2410
PC/pa
b. Mo a 3.0
FIGURE 13. EFFECT OF NOZZLE DIAMETER ON BASE PRESSURE,EXIT MACH NUMBER = 1. 78, CONICAL NOZZLES
23
2. 0 0/.2
0.
0.4
0&2
0 20 40 60 80 100 120 140 160 160 200 220
PC/ Pooa. M 2.5
go
0.6 N" I *e D / DS
2.7 0 0.25*2.7 0 0.20
0.4
0.2
0.1- - - - - - - - - - - - -
0 40 80 120 160 200 240 260 320 360 400 440
PC /Pas
FIGURE 14. EFFECT OF NOZZLE DIAMETER ON BASE PRESSURE,EXIT MACH NUMBER = 2.70, CONTOURED NOZZLES
24
02.7 20 0.100.5 - 2.7 20 0.20
27 20 0.30
20 0.20
0. --- 12. 20o 0.30
0 20 40 60 80 100 120 140 160
a. M 2.
EXIT ~ ~ ~ ~ 2. MAC NUBR0.20 CNCL OZE
0.5 27 20 .305
OA03.2 0 0.20
00.3
0.1
0 40 S0 120 160 200 240 280 320 360 400
PC /P**
00s3.2 0 '0.20A32 0 0.30
0.3
0.2
0.1
0 20 40 60 80 100 120 140 160 180 200
PC / Pooa. M a, 3.0
FIGURE 16. EFFECT OF NOZZLE DIAMETER ON BASE PRESSURE,EXIT MACH NUMBER = 3.20
26
0.5 2.70 20 0.100
0.4"
0.2
0.1NOTE: NOZZLE POSITIONS FORWARD OF
0 20 40 60 so 100 120 140 160PC / PC*
0.6 - - -
N. 0 D Ds X/D
052.70 20 0.10 0-0.400.4 0- 0.60
.4
0.2
0.1 -
NOTE: NOZZLE POSITIONS REAR OF MISSILE BASE01 2 0 40V 60 80 1 OO 120 140 160
PC /Pao
FIGURE 17. EFFECT OF NOZZLE POSITION ON BASE PRESSURE,I NOZZLE-BASE RATIO = 0. 10, MACH NUMBER = 2.50
27
w
0
MW431.
___ w *
Ns-3
zO -
0*zo0II
4v.
r'4N
0 0
cod / d
1.2
0.2
NOTE: NOZZLE POSITIONS REAR OF MISSILE BASE
0 20 40 60 so 100 120 140 160PB / P.
b.M N Dz3.50
0.5 X / DB m 1 * D 1 /D B
(D 2.70 20 0.200.4 El -0.60
.3
I NOTE: NOZZLE POSITIONS REAR OF MISSILE BASE
0 20 40 60 80 100 120 140
PC / Poonc. Moo =4.50
FIGURE 18. EFFECT OF NOZZLE POSITION ON BASE PRESSURE,NOZZLE-BASE RATIO = 0. 20 (Concluded)
29
00 I
040
0.33
0.7 -. o O
0.
NOTE: NOZZLE POSITIONS FORWARD OF MISSILE BASE
0 20 40 60 s0 100 120 140PC / P..
FIGURE 19. EFFECT OF NOZZLE POSITION ON BASE PRESSURE,NOZZLE-BASE RATIO = 0. 30, MACH NUMBER = 2.50
30
1OA
0.0
II 0.0.2
1 0..4
0.3
0.
M . . 0. D. /DI I BS
2.70 20 0.30NOTE: NOZZLE POSITIONS REAR OF MISSILE BASE
0 20 40 60 P/mso 100 120 140
FIGURE 19. EFFECT OF NOZZLE POSITION ON BASE PRESSURE,NOZZLE-BASE RATIO =0. 30, MACH NUMBER =2.50
31
Bibliography
Cortright, E. M., Jr., and Schroeder, A. H., "Investigation at MachNumber 1. 91 of Side and Base Pressure Distributions over ConicalBoattails without and with Jet Flow Issuing from Base," NACA RME51F26, September 1951.
Bromm, A. F., Jr., and O'Donnell, R. M., "Investigation at SupersonicSpeeds of the Effect of Jet Mach Number and Divergence Angle of theNozzle Upon the Pressure of the Base Annulus of a Body ofRevolution," NACA RM L54116, December 1954.
Reid, J., and Hastings, R. C., "The Effect of a Control Jet on Base Pressureof a Cylindrical Afterbody in a Supersonic Stream," Report No. Aero2621, December 1959, Royal Aircraft Establishment, Farnborough,England.
Hendersen, J. H., "Jet Effects on Base Pressures of Cylindrical and FlaredAfterbodies at Free-Stream Mach Numbers of 1.65, 1.82, and 2.21,"ARGMA TR 1G3R, June 1960, Army Rocket and Guided Missile Agency,Ordnance Missile Laboratories, Division, Systems Analysis Laboratory,Redstone Arsenal, Alabama.
Craven, A. H., Chester, D. H., and Graham, B. H., "Base Pressure atSupersonic Speeds in the Presence of a Supersonic Jet," CoA ReportNo. 144, AD No. 260621, December 1960, The College of Aeronautics,Cranfield.
Charczenko, N., and Hayes, C., "Jet Effects at Supersonic Speeds on Baseand Afterbody Pressures of a Missile Model Having Single and MultipleJets," NASA TN D-2046, November 1963, Langley Research Center,Hampton, Virginia.
Harries, M. H., "P. -ssure on Axisymmetric Base in a Transonic or SupersonicFree Stream in the Presence of a Jet," Report AE-584:1, March 1967,FFA The Aeronautical Research Institute of Sweden, Stockholm, Sweden.
Reid, J., "The Effect of Jet Temperature on Base Pressure," Royal AircraftEstablishment Technical Report 68176, July 1968.
Preceding page blank:33
AppendixTabulated Test Results
The following data were listed from computer equipment and the symbolsused to designate various parameters were selected to facilitate the use ofthis equipment. The following list identifies the symbols used in this portion ofthe report:
CPB Base pressure coefficient, B 1. 0.7 (MF) 2
CT Thrust coefficient, thrust/ [dynamic pressure x reference area]
D* Diameter of nozzle at the throat (in.)
DJ Diameter of nozzle at the exit plane (in.)
DB Reference diameter of body, 2. 50 in.
GJ Jet specific heat ratio
L Model length (in.)
MF Free stream Mach number
MJ Jet exit Mach number
PB Mean base pressure (psia)
PC Jet stagnation pressure (psia)
PF Free stream static pressure (psia)(PJ) (AJ)(MJ) 2
RMF Jet momentum fluxratio, (PF) (AB) (MF)2 where AJ = ir 2
AB = 7 "B 2, and PJ = jet static pressure
THEJ Divergence half-angle of nozzles (deg)
TOF Free stream static temperature (0 F)
RN Reynolds number per inch
XJ Location of nozzle exit plane relative to model base (in.)(negative positions rear of model base)
35Preceding page blank
The data are arranged according to the index given in Tables A-Ithrough A-III.
TABLE A-I. INDEX TO TABULATED DATA
Group M. 0.j Dj/D B Mo RN x 10 6
1A 1.0 0 0.10 2.50 0.471.0 0 0.10 3.00 0.51
1B 1.0 0 0.14 2.50 0.231.0 0 0.14 2.50 0.471.0 0 0.14 3.00 0.251.0 0 0.14 3.00 0.51IC .0 0 0.20 2.50 0.472 1.0 0 0.20 3.00 0.51
1.78 0 0.16 2.50 0.231.78 0 0.16 2.50 0.471.78 0 0.16 3.00 0.251.78 0 0.16 3.00 0.51
I21.78 0 0.20 2.50 0.51
1.78 0 0.20 2.50 0.47
1.78 0 0.20 3.00 0.25I 1.78 0 0.20 3.00 0.512C 1.78 5 0.20 2.50 0.47
1.78 5 0.20 3.00 0.511.78 20 0.10 2.50 0.471.78 20 0.10 3.00 0.51
2E 1.78 20 0.20 2.50 0.4778 20 0.20 3.00 0.51
2F 1.78 20 0.30 2.50 0.47A 1.78 20 0.30 3.00 0.513A 2.20 0 0.20 2.50 0.23
2.20 0 0.20 2.50 0.472.20 0 0.20 3.00 0.25
1 2.20 0 0.20 3.00 0.513B 2.20 20 0.20 2.50 0.47
2.20 20 0.20 3.00 0.51JA 2.70 0 0.20 2.50 0.23
2.70 0 0.20 2.50 0.512.70 0 0.20 3.00 0.252.70 0 0.20 3.00 0.51
36
I
TABLE A-I. INDEX TO TABULATED DATA (Concluded)
Group M 0 D /D B mo R x 10 6
____ I j'B RNlo
4B 2.70 0 0.25 2.50 0.232.70 0 0.25 2.50 0.47
4 2.70 0 0.25 3.00 0.251 2.70 0 0.25 3.00 0.51
4CD 2.70 10 0.20 2.50 0.472.70 10 0.20 3.00 0.512.70 15 0.20 2.50 0.472.70 15 0.20 3.00 0.512.70 20 0.20 2.50 0.472.70 20 0. 20 3.00 0. 542.70 20 0.20 3.50 0.50
2.70 20 0.20 4.00 0.502.70 20 0.20 4.50 0.49
4F 2.70 20 0.30 2.50 0.542.70 20 0.30 3.00 0.54
5A 3.20 0 0.20 2.50 0.233.20 0 0.20 2.50 0.473.20 0 0.20 3.00 0.25
I 3.20 0 0.20 3.00 0.515B 3.20 0 0.31 2.50 0.23
3.20 0 0.31 2.50 0.473.20 0 0.31 3.00 0.253.20 0 0.31 3.00 0.51
5C 3.20 20 0.20 2.50 0.476 3.20 20 0.20 3.00 0.51
6A 3.80 20 0.20 3.00 0.503.80 20 0.20 2.50 0.47
37
TABLE A-il. NOZZLE POSITION DATA
Group M. 0. Dj/ B M N (n) xN DB
7A 2.70 20 0.10 2.50 0. 55 x 10+6 -0.60-0.40
00.330.500.670.820.98
7B 2.70 20!020 2.50 0. 55 x 10+6 -0.60-0.40-0.20
00.330.500.670.820.98
3.50 0. 50 x 10t, -0.60-1.20
4.50 0. 49 x 10+1 -0.60-1.20
7C 2. 70 20 0.30 2.50 0. 551 lo10+ -0.60-0.40-0.20
00.330.500.670.82
38
TABL.,E A-HI. REYNOLDS NUMBER DATA
Group M. 0. D./D M R (in.)
&A 2.70 0 0.25 2.50 0.12 x 10+60.23 x 10+60. 35 x 10+ 10.47 x 10+6
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j 65
UNCLASSIFIEDsecurty Caselfieall,
DUUMENT CONTROL DATA. ifSeeullty clossi f eo of title. be* of abolt a" id ok adix * w~ must 11M aIIM014 whea A" 0wrf aca
*Caepafe.AaN#46 A J. RaPORT OCCURITY CLASGUPICAT~flN
Research and Engineering Directorate a UcauifeU. S. Army Missile Command a*OJRedstone Arsenal, Alabama 35809 N/A
MCIN0PO1' TITLK
INVESTIGATION OF THE EFFECT OF LOW THRUST LEVELS ON THE BASE PRESSUREOF A CYLINDRICAL BODY AT SUPERSONIC SPEEDS
4. OUICRiPTIVIK NOrall(7" o pme epwmd louiodahl)
Technical Report
T. A. MartinC. E. Brazzel
9000 REODATS T& TOTAL POO. OF PA49S 7b. NO. or RgePS
7 May 1970 1CONTRACT OR GRAM? NO. *a. ORgCINATOWS REKPORT NUM1119RISI1
&. PRJ9CTfNO. (DA) IM262301A206 RD-TR-70-.11
AMC Management Structure Code No. inb. R N18O(S)li (Anr .*6i monbm *61a o &*Met&"
5221. 11. 148 AD_________
'"Wo"tAeflT sbjc to special export controls and each transmittal to foreigngovernments or foreign nations may be made only with prior approval of this Command,AM: AMSMI-RD.
to. SUP01161AKNITARY NOT61 18 SPONSORING MILITARY ACTIVITY
None Same as No. 1
VS, ACITOACY
, Results of supersonic wind tunnel tests are presented which show the effectsof varying nozzle geometry, location, and supply pressure on the base pressure of acylindrical body at zero angle of attack. The purpose of the tests was to investigatethe parametric Influences 'an the regions where base pressure is near a minimum,which occurs in the lower range of thrust levels. A bibliography of relatedexperimental results is also included.
ID "o"01473 001EerlIAtl () USE J"N . "me" is UNCLASSIFIED 69Usifft aaufCINIO=
UNCLASSIFIED
4. , ,.. I I OIK A LINK aI MKSN C
KEY WORDS WOLE WT ROL2 WT ROLE[ WY-
Supersonic wind tunnel testsNozzle geometryLocationSupply pressureCylindrical body
70 UNCLASSIFIED70secwty MINIUMti