An escape system extraction rocket proposed for use on the Rotor Systems Research Aircraft was tested at Mach numbers of 0.1 and 0.3 through an angle of attack range from -2 deg to 102 deg and an angle of sideslip range from 0 deg to 15 deg in the Langley 7- by 10-foot high speed tunnel

Fox, C. H., Jr.

Huffman, J. K.

Satterthwaite, R. E.

English

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https://ntrs.nasa.gov/search.jsp?R=19770013081 2020-03-22T11:11:02+00:00Z
NASA TECHNICAL
	 NASA TM X -74009
MEMORANDUM
(NASA-TM-X-74 r10 q )	 LONGIT[I DINAL AND
	 N77-20025
c	 LATERAL-DIPECTIONAL STATIC AERODYNAMIC
C1ARACT F PISTICS OF AN TJNPOW r RFD FSCAoF
SYSTF4 FXTPAC T ION ROCKET MODEL (NASA)
	 26 p	 Unclas
>c	 RC A^I/MF All	 CSCL 01A G3/^2 22834
f--
Q
z LONGITUDINAL AND LATERAL-DIRECTIONAL STATIC AERODYNAMIC CHARACTERISTICS OF
AN UNPOWERED ESCAPE SYSTEM EXTRACTION ROCKET MODEL
by
Jarrett K. Huffman,
Charles H. Fox, Jr.,
and
	
Robert E. Satterthwaite 	 11
March 1977
This informal documentation medium is used to provide accelerated or
special release of techni-al information to selected users. The contents
may not meet NASA formal editing and publication standards, may be re-
vised, or may be incorporated in another publication.
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION
LANGLEY RESEARCH CENTER, HAMPTON, YIROAIA 23665
`	 APR 10,77
RECEIVED
NASA STI rACILITY ti
INPUT BRANCHt-.
RI.	 Report No. 2. Government Accession No. 3. Recipient's Catalog No.
NASA TM X-74009
4.	 Title and Subtitle
LONGITUDINAL AND LATERAL-DIRECTIONAL STATIC AERODYNAMIC
S. Report Date
March 1977
CHARACTERISTICS OF AN UNPOWERED ESCAPE SYSTEM EXTRACTION 6. Performing Organization Code
ROCKET MODEL
7. Author(s)
	
Jarrett K.	 Huffman,	 Char I es H.	 Fox,	 jr. , ana 8. Performing Organization Report No,
Robert E. Satterthwaite
10. Work Unit No.
9. Performing Organization Name and Address
NASA Langley Research Center
11. Contract or Grant No.Hampton, VA	 23665
13. Type of Report and Period Covered
Technical Memorandum
12. Sponsoring Agency Name and Address
National Aeronautics and Space Administration
Washington, DC	 20546 14. Sponsoring Agency Code
15. Supplementary Notes
16. Abstratz
An escape system extraction rocket proposed for use on the Rotor Systems Research
Aircraf^ was te8ted at Mach numbers of 0 -.1 and 0.3 thrsugh anoangle-of-attack range
from -2	 to 102	 and an angle-of-sideslip range from 0 	 to 15	 in the Langley 7- by
10-foot high speed tunnel. The data are presented without analysis in order to expedit
publication.
17. Key Words (Suggested by Authorls)) 18. Distribution Statement
Longitudinal aerodynamics
Lateral-directional aerodvnamics Unclassified-Unlimited
High angle of attack data
Subsonic Flow
Rockos
19. Security Clauit. (of this report) 20. Security Classif. (of this page) 21. No, of Pages 22.	 Price'
Unclassified Unclassified
23 $3.50
For sale by the National Technical Information Service, Spfingf
ABSTRACT
`
	
	 An escape system extraction rocket proposed for use on the Rotor
Systems Research Aircraft was tested at Mach numbers of 0.1 and 0.3
through an angle-of-attack range from -2° to 102° and an angle-of-
sideslip range from 0° to 15° in the Langley 7- by 10-foot high speed
tunnel. The data are presented without analysis in order to expedite
publication.
C
INTRODUCTION
The Rotor Systems Research Aircraft is a combined effort of the
U.S. Army and NASA. An emergency escape system for this aircraft was
proposed using an extraction rocket for each personnel station. A
hot gas launch system attached to the aircraft would initiate the separa-
tion of the extraction rocket from the aircraft. A wind tunnel test
program was initiated to obtain static aerodynamic data for input to a
digital computer simulation of the rocket and extracted crewman trajectory.
It is the purpose of this report to present, without analysis, the
static aerodynamic characteristics of this proposed extraction rocket.
The investigation was conducted in the bangley 7- by 10-foot high speed
tunnel at Mach numbers of 0.1 and 0.3 which correspond to Reynolds
numbers based on model reference diameter of 0.15 x 10 6 and 0.475 x 106,
respectively. The angle-of-attack range was from -2 0 to 1020 and the
angle-of-sideslip range was from 00 to 150.
SYMBOLS
The International System of Units, with the U.S. Customary Units
presented in parentheses, is used for the physical quantities in this
report. (See reference 1). Measurements and calculations were made
in the U.S. Customary Units. The data presented in this report are
referred to the body axis system as indicated in figure 1.
b	 model reference span, .0762 m (.25 ft)
CA	
q
axial force coefficient, Axial ForceS
C	 rolling moment coefficient, Rolling Moment1	 qSb
C	 ;itching moment coefficient, Pitching Moment
m	 qSd
Crr	normal force coefficient, Normal ForceS
Cn	yawing moment coefficient, Yaw
winng Moment
CY	side force coefficient, Side FoxS
d	 model reference diameter, .0762 n
M	 free stream Mach number
q	 free stream dynamic pressure, Pe
S	 model reference area, .00456 m2 (.049087 ft2)
a	 angle of attack, degrees
B	 angle of sideslip, degrees
DESCRIPTION OF MODEL
A full scale unpowered model was used in this study. A drawing
of the model is shown in figure 1.
The model consisted of a nose, which incorporated the rocket
nozzles, and a cylindrical center body, which was attached to a strain-
gage balance.
The nose could be set at different roll angles relative to the
centerbody. Since the centerbody was axisymmetric, the roll attitude
of the nose was used to define the roll orientation of the model,
3
v
APPARATUS, TESTS, AND CORRECTIONS
This investigation wad made in the Langley 7- by 10-foot high
speed tunnel which is a continuous flow atmospheric tunnel. Forces
4
and moments were measured by an internally mounted six-component
strain-gage balance. The pitch attitude of the model was measured
by an accelerometer mounted within the model. The pressure in the
balance chamber was also recorded, however n  corrections were made to
the data for chamber pressure.
The test was conducted at Mach number of 0.1 and 0.3 which
correspond to Reynolds numbers of 0.15 x 106 and 0.475 x 106 based
on d. The angle-of-attack range was from -20 to 102° and the angle-
of-sideslip range was from 0 0 to 150.
Two major test setups were employed during the test. For the
angle-of-attack range from -2 0 to 220 , the combined alpha and beta was
obtained using combinations of sting pitch and sting yaw. The sting
entered the model through the open base of the model.
The second test setup achieved combined alpha and beta using com-
binations of sting pitch and model roll. This setup divided the pitch
angle into three overlapping ranges of 330 to 570 , 55 . 5 0 to 79.5 0 , and
780 to 102 0 . The model roll angle was chosen for the midpoint of each
pitch range. Since the sideslip was achieved through a fixed model
roll for each pitch range, the sideslip angle was not constant. The
4	
sting entered the model through an opening in the top of the centerbody.
The base of the model was plugged; however, no base pressures were
measured. Note that the test technique employed for each pitch
range was to start with the model at the midpoint of the range, then
proceed to the lower limit of the range and take data as the pitch
angle was increased to the upper limit of the range.
PRESENTATION OF RESULTS
The longitudinal characteristics are presented in figure 2. The
lateral-directional characteristics are presented in figure 3. The
chamber pressure characteristics are presented in figure h.
Note that, d!ie to the test technique employed, there may be
anomalies between the data in the overlapped pitch range. These
anomalies are real anu result from the fact that, in one case the
overlap region was presumably approached with attached flow on the
model, whereas in the other case, the overlap region was presumably
approached with separated flow on the model.
The differences between the data at a Mach number of 0.1 and
at a Mach number of 0.3 are attributable primarily to Reynolds
number effects. (See reference 2.)
s,
REFERENCES
1. Mechtly, E. A.; The Internaticial System of Units NASA SP-7012,
1964.
2. Polhamus, Edward C.; Effect of Plow Incidence and Reynolds Number
on Low-Speed Aerodynamic Characteristics of Several Noncir--ular
Cylinders with Applications to Directional Stability and Spinning
NASA TR R-29, 1959•
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Figure 1. Drawings of the model tested.
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Longitudinal and lateral-directional static aerodynamic characteristics of an unpowered escape system extraction rocket model

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