Effect of canard oscillations on the vortical flowfield of a X-31A-like fighter aircraft model.

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by  Liu, Da-Ming.;Hebbar, S. K.;Platzer, Max Franz.

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Effect of Canard Oscillations on the
Vortical Flowfield of a X-31A-Like Fighter Aircraft Model
by
Liu, Da-Ming
Lieutenant Commander, R.O.C. Navy
B.S., Chung Cheng Institute of Technology ,1981
Submitted in partial fulfillment
of the requirements for the degree of
MASTER OF SCIENCE IN AERONAUTICAL ENGINEERING
from the
NAVAL POSTGRADUATE SCHOOL ^
^ ^
__ March !992
;
Department of Aeronautics and Astronautics
u
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I.SECURITYCLASSIFICATIONAUTHORITY 3.DISTRIBUTION/AVAILABILITYOFREPORT
Approvedfor publicrelease;distributionisunlimited.
DECLASSIFICATION/DOWNGRADINGSCHEDULE
).
PERFORMINGORGANIZATIONREPORTNUMBER(S) 5 MONITORINGORGANIZATIONREPORTNUMBER(S)
I.NAMEOFPERFORMINGORGANIZATION 6b OFFICESYMBOL 7a.NAMEOFMONITORINGORGANIZATION
avalPostgraduateSchool (Ifapplicable) NavalPostgraduateSchool
AA
c.ADDRESS{City,State,andZIPCode) 7b ADDRESS{City,State,andZIPCode)
lonterey.CA 93943-5000 Monterey,CA 93943-5000
a NAMEOFFUNDING/SPONSORING 8b OFFICESYMBOL 9.PROCUREMENTINSTRUMENTIDENTIFICATIONNUMBER
•RGANIZATION (Ifapplicable)
c ADDRESS(Crty,State,andZIPCode) 10 SOURCEOFFUNDINGNUMBERS
ProgramElementNo ProjectNo TasJiNo WorkUnitAccession
Number
1 TITLE(IncludeSecurityClassification)
ffectofCanardOscillationsontheVorticalFlowfieldof aX 31A likeFighterAircraftModel.(Unclaaaified)
2 PERSONALAUTHOR(S) Liu,Da-Ming
3a TYPEOFREPORT 13b.TIMECOVERED 14 DATEOFREPORT(year,month,day) 15 PAGECOUNT
[aster'sThesis From To MARCH 1992 129
SUPPLEMENTARYNOTATION
S.
ieviewsexpressedinthisthesisarethoseoftheauthoranddonotreflecttheofficialpolicyorpositionoftheDepartmentofDefenseortheU.S.
overnment.
7 COSATICODES 18 SUBJECTTERMS(continueonreverseifnecessaryandidentifybyblocknumber)
FIELD GROUP SUBGROUP Highangleofattackaerodynamic,effectofpitchrateandcanardoscillationsvortex
breakdown,flowvisualizationby dyeinjection,X-31A-likefighteraircraftmodel
9 ABSTRACT(continueonreverseifnecessaryandidentifybyblocknumber)
flowvisualizationinvestigationwascarriedoutintheNavalPostgraduateSchoolwatertunnelusingdyeinjectiontechniquetostudythe
Tectsofoscillatingaclose-coupledcanardona2.3%scalemodelofaX 31A-likefighteraircraft.Thisinvestigationfocuasedprimarilyonthe
Tectsofcanardoscillationsonthebreakdowncharacteristicsofthewingrootvortexforbothstaticanddynamicconditionsofthemodelatzero
deslipangle.Themainresultsofthisfirstofakindwatertunnelvisualizationsuggestthatforthestaticconditionsofthe modelthelow
equencycanardoscillationstendtodesabilize/augmentwingvortexcore,i.e.,promote/delayburstingofwingvortex,thedynamictestsindicate
latthelargeamplitudelowfrequencyoscillationsofthecanardinteracfavorablywiththewingvorticalflowfieldtodelay vortexbursting
oringbothpitch-upandpitch-downmotions.
D DISTRIBUTION/AVAILABILITYOFABSTRACT 21.ABSTRACTSECURITYCLASSIFICATION
PI UNCLASSIFIED/UNLIMITED [J SAMEASREPORT IH DTICUSERS UNC1ASSIFIED
>a NAMEOFRESPONSIBLE INDIVIDUAL 22b TELEPHONE(IncludeAreacode) 22c OFFICESYMBOL
K.Hebbar [phone] AA/HB
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ABSTRACT
A flow visualization investigation wascarried outintheNaval PostgraduateSchool
watertunnelusingdyeinjection technique to study the effects ofoscillatinga close-coupled
canard on a 2.3% scale model of a X-31A-like fighter aircraft. This investigation focussed
primarily on the effects ofcanard oscillations on thebreakdown characteristics ofthe wing
root vortex forboth static and dynamic conditions ofthe model at zero sideslip angle. The
main results ofthis first ofa kind water tunnel visualization data suggest that for the static
conditions of the model the low frequency/ high frequency canard oscillations tend to
destabilize/ augment wing vortex core, i.e., promote/ delay bursting of the wing vortex.
The dynamic tests indicate that the large amplitude low frequency oscillations of the
canard interact favorably with the wing vortical flowfield to delay vortex bursting during
both pitch-up and pitch-down motions.
in
c.i
TABLE OF CONTENTS
INTRODUCTION
I. 1
BACKGROUND
A.
1
B. OSCILLATING CANARD 4
STATEMENT OF PURPOSE
C. 5
EXPERIMENTAL APPARATUS
II. 6
WATER TUNNEL
A. 6
B. X-31A-LIKE MODEL 7
MODEL MOUNTING
C. 11
EXPERIMENTAL PROCEDURE
III. 12
EXPERIMENTS
A. 12
B. REDUCED PITCH RATE SIMULATION 12
C. DATA ACQUISITION AND REDUCTION 15
D. METHOD OF PHOTOGRAPHY 16
IV. RESULTS AND DISCUSSION 19
IV
UammmZ varcMUUATE SCHOOL
MONTIRgy CA
93943-5101
A. EFFECTS OF AOA ON THE WING FLOWFIELD OF X-31A- LIKE
MODEL
20
B. EFFECTS OF STATIC CANARD DEFLECTION ANGLE ON THE
WING FLOWFIELD OF THE STATIC MODEL 21
1. Effects of Postive Canard Deflection Angle 21
2. Effects of Negative Canard Deflection Angle 22
C. Effects of Canard Oscillation on the Wing Flowfield of the Static
Model 22
1. Effects of Small Amplitude Canard Oscillations 23
2. Effects of Large Amplitude Canard Oscillations 23
D. DYNAMIC EFFECTS OF AOA ON THE WING FLOWFIELD OF
THE PITCHING MODEL WITH STATIC CANARD 24
EFFECTS OF CANARD OSCILLATIONS ON THE WING
E.
FLOWFIELD OF THE PITCHING MODEL 25
1. Effects of Small Amplitude Low Frequency Canard Oscillations . . 25
2. Effects of Small Amplitude High Frequency Canard Oscillations 26
.
3. Effects Large Amplitude Low Frequency Canard Oscillations .... 27
4. Effects of Large Amplitude High Frequency Canard Oscillations 27
.
«
V. CONCLUSIONS AND RECOMMENDATIONS 28
LIST OF REFERENCES 30
APPENDIX A. EXPERIMENTAL RESULTS (TABLES) 32
APPENDIX B. EXPERIMENTAL RESULTS (PHOTOGRAPHS) 37
APPENDIX C. EXPERIMENTAL RESULTS (GRAPHS) 110
INITIAL DISTRIBUTION LIST 119
VI