NASA TECHNICALMEMORANDUMD5 Bulldozer and an MI09 Self-Propelled 155 MM Howitzer. Models of these two configurations were sized to maximize Reynolds number in the test section for the
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i NASA TECHNICAL NASA TM X-62.330MEMORANDUM
t:dASA°T_-I-62330) WIND TUtiJiEL !_74-15973¢O
-- IBVES_IGATIOB OF AERODYH&BIC
a_ CHARACTERISTICS OF A SCALE BODEL OF A D5_- BOLLDOZER ABD a_ B109 SELF-P_OFE£LED 155 gnclas
io (HASA) 10g p tic $7.2 =. CSCL 20D G3/12 28336 _.02 _
NN
WIND TUNNEL I_IVESTIGATION OF AERODYNAMIC CHARACTERISTICS
OF A SCALE MODEL OF A D$ BULLDOZER AND AN
; MI09 SELF-PROPELLED 155 MM HOWITZER _:\
'_ Georgene H. Laub and Hifu M. Kodani
• _,!_ andAmesResearchCenter _ ,_/2 IJ. S. Arm/,Air Mobility R&D Laboratory . .
Moffet; Field, California 94035 _¢,.. __O/_, _
\t
_ '_" i'," January 1974
https://ntrs.nasa.gov/search.jsp?R=19740007860 2020-03-23T12:40:03+00:00Z
|WIN_ TD_NEL iNVESTIGATION OF AERODYNAMIC
CHARACTERISTICS OF A SCALE MODEL OF A
D5 BULLDOZER AND AN MI09 SELF-PROPELLED 155 MM tiOW!TZER
"+i
J by
• Georgene H. Laub
And
Hifu M. Kodani
_. SUMMARY
Wind tunnel tests were conducted on a scale model of a D5 bulldozer "
_-+ and an M109 Self-Propelled 155 MM Howitzer to determine the aerodynamic _
•_"- characteristics of these typlcal externally-suspended heavy llft hell-
_+_i_++ copter :argo configurations. Tests were made over a large range of
+_7 pitch and yaw attitudes at a nominal Reynolds number per unit length
: of 1.5 X 10 6 . This report presents the aerodynamic data obtained from
\
!: the tests.
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+
] 974007860-002
J
INTRODUCTION 1!
Operational requirements of heavy lift helicopters require the
transportation of large cargo items at moderately high speeds. The i
aerodynamic characteristics of such externally-suspended cargo can
adversely affect the stability of the helicopter-sling cargo system.
A lack of experimental data on typical large cargo items seriously
hinders theoretical predictions of the effects of such configurations
on the performance and dynamics of the complete system.
Wind tunnel tests were made on a model of a D5 bulldozer and an
MI09 Self-Propelled 155 MM Howitzer in the Army Air Mobility Research
and Development Laboratory 7XI0 Foot Wind Tunnel. The purpose of this
report is to present the aerodynamic data obtained from tests on these
two models•
#
NOTATION
b span
c chord
CD drag coefficient, D/qS
CL lift coefficient, L/qS
CPM pitching moment coefficient, PH/qSc
CRM rolling moment coefficient, ILq/qSb
CY side force coefficient, Y/qSJ,
CYM yawing moment coefficient, YM/qSb " ....
, D drag force
L _
;J
1974007860-003
, L lift force
PM pitching moment
q dynamic pressureI
RM rolling moment
Y side force
YM yawing moment
0 Fitch angle
yaw anglei
Positive Directions as ShownJ
L.
L
" D
0
ION i
' DESCRIPTION OF MODELS
Two heavy llft helicopter externally-suspended cargo ite_q repre-
sentative of those currently in wide use throughout the military
transport system were se acted for thls wind tunnel investigation - a
D5 Bulldozer and an MI09 Self-Propelled 155 MM Howitzer. Models of
these two configurations were sized to maximize Reynolds number in the
test section for the full range of model pitch and yaw angles. The
i bulldozer model, constructed with a detachable blade, was i/5 stile;
the MI09 model was 1/8 scale. Photographs of each model are presented
i in Figure_ 1 and 2. The moJels were sting mounted and, with the excep-tion of the bulldozer/blade configuration, tested in both a forward and
reversed position. Model loads were measured using an Internal strain
_ gage balance. Photographs showing the models mounted in the tunnel are
presented in Figures 3 and 4.?
- _ TEST AND PROCEDURES
The three D5 Bulldozer model configurations and the two Kl09 model
configurations tested in the 7X10 foot wind tunnel are shown in Figures
: 3 avd 4. Except for two tests, the Kl09 model was tested without thef
_ machine gun. Yaw attitude was varied using the tunnel turntable system;)
pitch attitude was varied using the pitching mechanism of the sting/strut
support system. Model aerodynamic loa_ ware _ured using an internalq_
strain gage balance; model moment reference center, as shown In Figure 5,
. and straln gage balance center coincided.
1974007860-005
Except as noted, the tests were conducted at a nominal tunnel
i dynamic pressure of 3591 N/m 2 (75psf) with a corresponding Reynolds• number based on unit length of 1.5x106. Test data were taken varying
pitch attitude at constant angles of yaw through a yaw range of -90°
to 95°. Negative sting pitch angles were limited to -12 ° to avoid model-
strut interference effects due to proximity of the model with the strut.
The models, including strain gage balance, were rotated 180° on the sting
and tested in this inverted position to provide data through a model
pitch range of -40 ° to 40°. As a result of this inversion, two sets of
data were obtained in the -12 ° to 12° pitch attitude range.
Model configurations and attitudes were necessarily held to a mini-
mum on the following additional comparative-type tests. Tests with the
machine gun mounted on the 14109 model were limited to yaw attitudes of
I 0 ° and 90 ° and a pitch angle range of -12 ° to 40 °. To provide an indica-
tion of Reynolds number effect the three forward model configurations were
tested at 1197 N/m 2 (25psf) or a Reynolds number of 0.9x106 based on unit
length, These testa were made at 8 yaw a_titude of 0 ° and through the
-12 ° to .0° pitch &ngle ranse. Two tests on the MI09 forward configura-
tion were repeated at O" and 90" yaw attitude thzough the -12 ° to 40 °
pitch angle range for a check on data repeatability.
PRESENTATION OF DATA
4, The results of the tests on the models are pruented in tabular form;
tables and model test attitude8 ate indexed in Table I. _,:_:,
Model aerodynsuLc data are pzuented as full scale ae_odTutu4c
coefficients; chase cosf_icient8 are based on unit valu_ for chord,
5
1974007860-006
II
span, and area to facilitate, upon multiplication by the dynami(, pres-
sure, a direct conversion to the aerodynamic loads. The full scalet
aerodynamic coefficients presented in the tables were obtained by multi-
plying the model force coefficients by the scale factor squared and
I model moment coeflicients by scale factor cubed. The appropriate con-
stants are listed below. I
|Model Force Data Moment Data
(scale factor) 2 (scale factor) ?
D5 Bulldozer 25.0 125.0
MI09 64.0 512.0
_ Forces and moments are resolved with respect to wind axes; moments are
T referenced to the moment reference center shown in Figure 5. Data from
the additional tests (Tables VII, VIII, and IX) are presented, as thei
aerodynamic coefficients and also include the incremental value between
; these data and the comparative data from Tables II thru VI. The non-
" aerodynamic shape of the model, Insuins rough tunnel flow and model
vibrations resulted in a correspondingly large data repeatability
scatter band especially at the more extreme ansles. Data from the
testa to evaluate the effect of Reynolds number and the effect of
_ machine sun were essentially lost in the data repeatability scatter;
band. Since model testtns positions were selected to exclude those
\ _ reslons necessitating model-strut interference effect corrections, none
.,are accounted for in the data.
• To provide a visual indication of the aerodynamic characteristics
6
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1974007860-007
|of the five configurations tested, some data were selected from Tables |
II through Vl and plotted. These data are pcesented _n Figures 6 through
I0. Parts (a) and (b) of each of these figures present the force and
i moment coefficients plotted againet pitch angle at 0 degrees yaw angle.
The force and moment coefficient variation with yaw angle are shown in
parts (c) and (d) for pitc_ angles of -16, 0, and 16 degrees.
4
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