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 _

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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/_, _

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_ '_" 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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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 _

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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

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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.

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