Hypersonic static stability investigation of Tomahawk rocket mode

Merz, G. H.

English

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AEDC-TR-66-148 A/66 39857
(ACCESSION NUMBER!
(NASA CR OR TMX O*"Arf (CATEGORY*
HYPERSONIC STATIC STABILITY INVESTIGATION OF A
TOMAHAWK 20-PERCENT-SCALE MODEL
Glenn H. Merz
ARO, Inc.
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August 1966
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AEDC-TR-66-148
HYPERSONIC STATIC STABILITY INVESTIGATION OF A
TOMAHAWK 20-PERCENT-SCALE MODEL
Glenn H. Merz
ARO, Inc.
Distribution of this document is unlimited.
AEDC-TR-66-148
FOREWORD
The work reported herein was done at the request of NASA,
Goddard Space Flight Center, for Fairchild-Hiller Corporation
under System 92IE.
The results of tests presented were obtained by ARO, Inc.
(a subsidiary of Sverdrup & Parcel and Associates, Inc. ), contract
operator of the Arnold Engineering Development Center (AEDC),
Air Force Systems Command (AFSC), Arnold Air Force Station,
Tennessee, under Contract AF40(600)- 1200. The test was conducted
from May 27 to June 2, 1966, under ARO Project No. VB1686, and
the manuscript was submitted for publication on July 14, 1966.
The author wishes to thank L. L. Trimmer, ARO, Inc. , for his
technical assistance during these tests.
This technical report has been reviewed and is approved.
Donald E. Beitsch Leonard T. Glaser
Major, USAF Colonel, USAF
AF Representative, VKF Director of Test
Directorate of Test
11
AEDC-TR-66-148
ABSTRACT
An experimental investigation was conducted to obtain detailed
static stability, induced roll and yaw, and roll forcing information
on several configurations of a Tomahawk 20-percent-scale model.
Tests were conducted at nominal Mach numbers of 6 and 8, free-
stream Reynolds numbers of 2. 5 x 10^ and 5.0 x 10^ per foot, angles
of attack from -2 to 14 deg, and roll angles from 0 to 90 deg.
Selected results are presented to illustrate types and quality of data
obtained.
111
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AEDC-TR-66 -148
CONTENTS
Page
ABSTRACT iii
NOMENCLATURE vi
I. INTRODUCTION :
IL APPARATUS
2. 1 Models I
2.2 Wind Tunnel 1
2. 3 Instrumentation 2
III. TEST CONDITIONS 2
IV. RESULTS AND DISCUSSION 2
ILLUSTRATIONS
Figure
1. Model Photograph 5
2. Model Details 6
3. Tunnel B 7
4. Effect of Model Length on Longitudinal Stability
Characteristics at Mach 6, Zero Roll,
Re m / f t = 2.5 x 106 . 8i
5. Effect of Mach Number on Longitudinal Stability
Characteristics of Configuration NjE2BiF},
Zero Roll, Re^ / f t = 2. 5 x 106 9
6. Effect of Roll Angle on Lateral Stability
Characteristics of Configurations NiE2B;[Fi
and N1E2B1F2 at Mach 6, Re^/f t = 2. 5 x 106 10
7. Effect of Angle of Attack on Lateral Stability
Characteristics of Configurations NiE 2 BjFi
andN1E2B1F2 at Mach 6, Re^/ft = 2. 5 x 106 11
TABLE
I. Test Summary 12
AEDC-TR-66-148
NOMENCLATURE
Cjg Rolling-moment coefficient, rolling moment/q^Sd
Cm Pitching-moment coefficient, pitching moment*/q^Sd
C^r Normal-force coefficient, normal force*/qODS
Cn Yawing-moment coefficient, yawing moment*/q00Sd
Cy Side-force coefficient, side force*/q00S
AC* Differential rolling-moment coefficient, Cn - Cnxa *-a = 0
ACn Differential yawing-moment coefficient, Cn - Cna a = 0
ACv Differential side-force coefficient, Cv " CvY i
 a i a = o
d Model centerbody diameter, 1. 80 in.
M,,, Free-stream Mach number
P Tunnel stagnation pressure, psia
qm Free-stream dynamic pressure, psia
Re^ Free-stream Reynolds number, ft"
S Model centerbody cross-sectional area, 2. 545 in. ^
TQ Tunnel stagnation temperature, °R
Xcp Center of pressure, 10. 539 + Cj^/C-j^, diameter from base
a Angle of attack, deg
<j> Roll angle, deg
cMeasured in ballistic axis
V 1
AEDC-TR-66 -148
SECTION I
INTRODUCTION
The purpose of these tests was to obtain detailed static stability,
induced roll and yaw, and roll forcing information on a Tomahawk
rocket vehicle 20-percent-scale model at Mach 6 and 8. Model center-
body extensions were used to obtain configurations of three different
lengths. The medium length model was tested with three nose and three
fin configurations. Induced roll and yaw tests were conducted only at
Mach 6.
/ /
Tests were conducted in the von Karman Gas Dynamics Facility
(VKF) 50-in. hypersonic tunnel (Gas Dynamic Wind Tunnel, Hypersonic
(B)) at Mach numbers of 6 and 8, free-stream unit Reynolds numbers of
2. 5 x 106 and 5. 0 x 106, angles of attack from -2 to 14 deg, and roll
angles from 0 to 90 deg.
SECTION II
APPARATUS
2.1 MODELS
Model photographs and details are shown in Figs. 1 and 2. The
various configurations consisted of three nose sections, two ogive and
one conical; three centerbody extensions; and three sets of flaps, two
without cant and one with a 1-deg positive cant.
2.2 WIND TUNNEL
Tunnel B is a 50-in. -diam continuous flow, closed-circuit, variable
density wind tunnel equipped with interchangeable Mach 6 and 8 axisym-
metric, contoured nozzles. It operates at nominal Mach numbers of 6
and 8 at stagnation pressures from 20 to 280 psia and from 50 to 900 psia,
respectively, at temperatures up to 1350°R.
Figure 3 shows the tunnel and its associated equipment. As shown
in this figure, the model may be injected into the tunnel for a test run
and then retracted from the test section for model changes without inter-
rupting tunnel airflow.
A E D C - T R - 6 6 - 1 4 8
2.3 INSTRUMENTATION
A six-component, moment-type, strain-gage balance was used to
measure model forces and moments. Prior to testing, a static calibra-
tion was performed using combined loads of the magnitude anticipated
during this test. The expected deviations, based on this calibration,
are summarized below:
Component Deviation
Normal Force ±0. 15 Ib
Pitching Moment ±0. 50 in. -Ib
Side Force ±0. 05 Ib
Yawing Moment ±0. 15 in. -Ib
Rolling Moment ±0. 05 in. -Ib
The data presented in Section IV were obtained by rolling the model
on the balance to obtain ballistic axes data directly; thus, the above-
mentioned deviations apply directly to the data.
SECTION III
TEST CONDITIONS
Conditions used during the tests are summarized as follows:
Configuration M^ Po, psia To, °R Re., x ID"6
N1E2B1F1 6 .06 280 860 5.0
All ' 6. 03 150 860 2. 5
All 7 .99 545 1310 2.5
SECTION IV
RESULTS AND DISCUSSION
Selected data at Mach 6, zero roll, Re^/ft = 2. 5 x 10^ are presented
in Fig. 4 to illustrate types of data obtained for various length models.
As would be expected, the center of pressure moved forward on the model
as the length was increased. Typical data for the basic configuration are
presented in Fig. 5 to illustrate the effect of Mach number on the stability
characteristics.
Figure 6 is a summary of the Mach 6 lateral stability data at various
roll angles. Canting the fins 1 deg produced a significant change in the
AEDC-TR-66-148
rolling-moment data over the entire angle-of-attack range. However,
it did not appreciably alter the side-force and yawing-moment data at
the lower angles of attack.
The differential lateral stability characteristics are presented in
Fig. 7. These coefficients were computed by subtracting the zero
angle-of-attack data from the data obtained at various angles of attack.
The canted fins had little effect on -the incremental forces and moments
produced by changing angle of attack.
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AEDC-TR-66 -148
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AEDC-TR-66 -148
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AEDC-TR-66 -148
Screen Section -, Nozzle Section -, Test Section-?
Mach 6 or 8 / Quartz Windows —,
Diffuser Section
Tank Access Floor—'
- Ground Floor
/ - Relief Valve
i— Tank Entrance
Tunnel Assembly
Windows for Model Inspection
or Photography
Windows for
Shadowgraph /Schlieren
Photography
Tank Entrance Door
for Model Installation
or Inspection
Model Injection and
Pitch Mechanism
Tunnel Test Section
Fig. 3 Tunnel B
A E D C - T R - 6 6 - 1 4 8
-1.0
-16.0
10.0
« S
fe t> 6.0
S.I
O Q
0 2 4 6 8 1 0 1 2 1 4
Angle of Attack, a, deg
Fig. 4 Effect of Model Length on Longitudinal Stability Characteristics at
Mach 6, Zero Roll, Re^/f t = 2.5 x 106
A E D C - T R - 6 6 - 1 4 8
-1.0
-16.0
10.0
s
? 4 6 8
Angle of Attack, a, deg
10 1?
Fig. 5 Effect of Mach Number on Longitudinal Stability Characteristics of
Configuration NiE2BiFi, Zero Roll, Re^/ft = 2.5 x 106
AEDC-TR-66-148
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12
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DOCUMENT CONTROL DATA • R&D
(Secunly clateillcation of title body of abstract and indexing annotation must be entered when the overall report it claetilied)
1 OPir . lNATIN G A C T I V I T Y (Corporate author}
Arnold Engineering Development Center
ARO, Inc., Operating Contractor
Arnold Air Force Station, Tennessee
2 a REPORT S E C U R I T Y C L A S S I F I C A T I O N
UNCLASSIFIED
26 GROUP
N/A
3 REPORT TITLE
HYPERSONIC STATIC STABILITY INVESTIGATION OF A TOMAHAWK 20-PERCENT-
SCALE MODEL
4 DESCRIPTIVE NOTES (Type ol report and inclusive date*)
N/A
5 AUTHORfS; (Latt name, lint name. Initial)
Merz, Glenn H., ARO, Inc.
6 REPORT DATE
August 1966
Ba C O N T R A C T OR GRANT NO.
AF40(600)-1200
«•• System 92 IE
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7a T O T A L NO OF PAGES 76. NO OF REPS
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AEDC-TR-66-148
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this report)
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10 AVAILABIL ITY /L IMITATION NOTICES
Distribution of this document is unlimited and qualified users may
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12 SPONSORING MILITARY ACTIVITY National
Aeronautics and Space Administration
(NASA) Goddard Space Flight Center
Greenbelt, Maryland
11 SUPPLEMENTARY NOTES
N/A
13 ABSTRACT
An experimental investigation was conducted to obtain detailed
static stability, induced roll and yaw, and roll forcing information
on several configurations of a Tomahawk 20-percent-scale model. Tests
were conducted at nominal Mach numbers of 6 and 8, free-stream
Reynolds numbers of 2.5 x 10^ and 5.0 x 10^ per foot, angles of attack
from -2 to 14 deg, and roll angles from 0 to 90 deg. Selected results
are presented to illustrate types and quality of data obtained.
DD FORM1 JAN 84 1473
Security Classification
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KEY WORDS
LINK A
ROLE WT
LINK B LINK C
Tomahawk
static stability
hypersonic flow
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Hypersonic static stability investigation of a Tomahawk 20-percent-scale model Technical report, 27 May - 2 Jun. 1966

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