Heitmeyer, John C

English

NASA Technical Reports Server

&-
RESEARCHMEMORANDUM‘
LIFT, DRAG,ANDPITCHINGMOMENTOF LOW-ASPECT-RATIOWINGS
AT SUBSONICANDSUPERSONICSPEEDS-
BODYOFREVOLUTION
By JohnC. Heitmeyqr
‘+.ssi ~.’Ames-Aer~na~~~~ @bora ory
k ..,.: t%lif.Lkis”’i%d J
~~~ff3@--.,h:j~,$fiiic */*g “
By ~% %6 +
...............
,.:.. .,,,,...
..............................!%ADE OF UFF}CEIt k.Atilt, G CHANGE] %
.. .. . . . . . . . . . . . . . . . . .
.. . . ..~..Q.pA ~ (# )
Diii- .... “..’” .“”””””””
CLA8SIF5D KKUKSIW
Morna!ionaM4MnsLb Natfwd DXe5saofUn UnftadStates WIMI tim
m Ss. rminnammslmortbwelntkmof fmcdentmln any
nmmmrlamma.u
InfOrmallOn60 CIaMined
Smas,wrfate Ck-ulmo- ~ * d navalMrvfcesof ttd Unlkd
llmref&mdf0unftdstah9 cst&,8ns0ftihtityti
NAT ONAL ADVISORY COMMITTEE
FOR AERONAUTICS
WASHINGTON
October4, 1951
—
https://ntrs.nasa.gov/search.jsp?R=19930086865 2020-06-17T13:35:03+00:00Z
NACARMA51H22
TECHLIBRARYWE, NM
Illllllllilllllllllllllllllllllllloi4iiilii
NATIONALADVISORYCOMMITTEEFORAERONAUTICS
RESEARCHMEMORKKDUM
LIIT,DRAG,ANDPITCHINGMOMENTOF LOW-ASPECT+ATIOWINGS
AT SUBSONICANDSUPERSONICSPEEDS–
B9DYOFREVOLUTION
ByJohnC.Heitmeyer
SUMMARY
Thelift,drag,andpitchingmomentofa bodyof revolutionare
presentedforMachnumbersfrom0.60to0.92andfrom1.20to 1.70.
Thesedatawereobtainedat testReynoldsnrmibersof0.64 million,
1.02million,and1.59 million.
INTRODUCTION
A researchprogramis inprogressat theAmesAeronauticalLabora-
torytoascertainexperimentallyat subsonicandsupersonicMachnumbers
thecharacteristicsofwingsof interestin thedesignofhig~peed
fighterairplanes.Theresultsof thisprogramarepresentedinrefer-
ences1 to 12. Thesereferencespresenthelift,drag,andpitching-
momentcharacteristicsofwin@mdy combinationsemployingwingsdesigned
specificallyto studytheeffectsofvariationsinplanform,twist,
cember,andthickmess.Theshapeof thebodywasderivedfromtheoreti-
calconsiderationfminimumpressuredragat supersonicspeedsfora
givenlengthandvolume.Thisreportpresentstheresultsoftestsof
b
z
M
thebodyalone.As inreferences1 to 12,thedatahereinare
withoutanalysisto expeditepublication.
NOTATION
actuallengthofbody
lengthofbody
Machnumber
includingportionremovedtoaccommodate
‘: F’EJUMNENT%:
- “’0”
presented
sting ;-,’”’.“,,
u’
f
. ... ...
.:.,, -
.
‘.
.; :
. .3.
--
—
2q
R
r
r.
s
x
a
Go
CL
cm
Miii%%%%%?hb
free-streamdynsmicpressure
Reynoldsnumberbasedon themaximumbody
radihsofbody
maximumbodyradius
maximumbodycross-sectionalarea
longitudinaldistancefromnoseofbody
angleofattackofbodyaxisjdegrees
NACARMA51H22
diameter
dxagcoefficient
()
drag
~
liftcoefficient
()
lift
w
pitchi~omentcoefficient(
pitchingmoment
qSb )
mPARATus
WindTunnelandEquipment
TheexperimentalinvestigationwasconductedintheAmes
6-by6-foo;supersonicwind~unnel.Inthiswindtunnel,theMach
numbercanbe variedcontinuouslyandthestagnationpressurecanbe
regulatedtomaintaina giventestReynoldsnumber.Theairisdried
topreventformationof condensationshocks.Furtherinformation
thiswindtunnelIspresentedinreference13.
Themodelwasstingmountedinthetunnel,thediameterofthe
stingbeingabout93 percentof thediameterofthebodybase. The
pitchplaneofthemodelsupportwashorizontal.A &inc&diameter,
fo~omponent,strain-gagebalance,enclosedwithinthebodyofthe
model,wasusedtomeasuretheaerodynamicforcesandmoments.This
balanceisdescribedingreaterdetailinreference14.
.
.
—
—
tNACARMA51H22
~
Model
A planviewofthemodelandcertainmodeldimensionsaregivenin
figure1. Otherimportantgeometricharacteristicsof themodelareas
follows:
body
Actualfinenessratio(basedon lengthb;
fig.1) . . . . . . . . . . . . . l . . . , . . . . . 9.86
Finenessratio(basedonlengthZ;fig.1) . . . . . . 12.5
Cross-sectionshape. . . . . . . . . . . . . . . . Circular
Maximumcross-sectionalarea,squarefeet. . . . . . 0.I-235 .
Distancetothemomentcenterfromnose,feet. . . . . 2.k~
Thebodysparwassteelandwascoveredwithaluminumto formthe
contours.
TESTSANDPROCEDURE
RangeofTestVariables
Theaerodynamiccharacteristicsof themodel(asa functionof
angleofattack)wereinvestigatedfora rangeofMachnunibersfrom
0.60toO.~ andfroml.m to 1.70. DatawereobtainedatReynolds
numbersof0.64 million,1.o2million,and1.59
ReductionofData
Factorswhichcouldaffecttheaccuracyof
million.
theseresults,together
withthecorrectionsapplied,arediscussedinthefollowingparagraphs:
Ttmnel+wall.interference.—No correctionsweremadeto theSU>
sonicresultsfortheinducedeffectsof thetunnelwallsresultingfrom
liftonthemodelsincetheseeffectswerenegligible.
Theeffectsof constrictionf theflowat subsonicspeedsby the
tunnelwallswere takenintoaccountby themethodsof reference15.
Thiscorrectionwascalculatedforconditionsat zerosingleofattack
andwasappliedthroughouttheangl=f+ttackrange.At a Machnuiber
ofO.~, thiscorrectionamountedto aboutl.>percentincreaseinthe
Machnuniberandinthedynamicpressureoverthatdeterminedfroma
calibrationf thewindtunnelwithouta modelinplace.
Forthetestsat supersonicspeeds,thereflectionfromthetunnel
wallsof theMachwaveorig se ofthebodydidnotcross
4themodel.No corrections
effects.
~
NACARMA51H22
wererequired,therefore,fortunnel+ll
Streamvariations.-No correctionsweremadetothesubsonicdata
ofthepresentreportfortheeffectsofthestreaminclinationa d
streamcurvatureinthetunnelairstream.Theeffectsof thesestream
irregularitiesuponthemeasuredcharacteristicsofthebodyshouldbe
small,sincereferences8 to M indicateonlya smalleffectuponthe
measuredcharacteristicsofwing-bodycombinations.At subsonicspeeds,
thelongitudinalvariationofstaticpressureintheregionof themodel
isnotknownaccuratelyatpresent,buta preliminarysurveyhasindi-
catedthatitislessthan2-percentofthedynamicpressure.No
correctionforthiseffectwasmade.
A surveyoftheairstreaminthe6-by 6-footsupersonicwind
tunnelat supersonicspeeds(reference13)hasshowna streamcurvatme
onlyintheyawplaneof themodel.Theeffectsof thiscurvatureon
themeasuredcharacteristicsof thepresentmodelarenotknown,butare
believedtobe negligible.Thesurveyalsoindicatedthatthereisa
stati~pressurevariationinthetestsectionof sufficientmagnitude
toaffect hedragresults.A correctionwasaddedtothemeasured
drag coefficient,herefore,toaccountforthelongitudinalbuoyancy
causedby thisstatic-pressurevariation.Thiscorrectionvariedfrom
asmuchas+.016 at a Machnumberof 1.30to0.012at a Machnumber
of 1.70.
SuPPortinterferenceO-At subsonicspeeds,theeffectsof support
interferenceon theaerodynamiccharacteristicsofthemodelarenot
known.Forthepresentmodel,itisbelievedthatsucheffectscon-
sistedprimarilyofa changeinthepressureat thebaseof themodel.
Inan effort ocorrectat leastpartiallyforthissupportinterfez=
ence,thebasepressurewasmeasuredandthedragdatawereadjustedto
correspondtoa basepressurequalto thestaticpressureofthefree
stream.
At supersonicspeeds,theeffectsof supportinterferencefora
body+tingconfigurationsimilarto thatofthepresentmodelareshown
by reference16 tobe confinedtoa changeinbasepressure.Thepr~
viouslymentionedadjustmentofthedragforbasepressure,therefore,
wasalsoappliedat supersonicspeeds.
RESULTS
Theresultsarepresentedinthisreportwithoutanalysisinorder
to expeditepublication.Thevariationof liftcoefficient,&ragcoef-
ficieirt,andpitchi~omentcoefficientwithangleofattackatReynolds
.
.
.
NACARMA51H22
u
5
numbersof0.64million,1.02million,and1.59 millionandatMach
nunibersfromO.60to 1.70 areshowninfigure2.
.
Ames
1.
2.
.
. 3*
4.
5.
.
79
AeronauticalLaboratory,
NationalAdvisory CommitteeforAeronautics,
MoffettField,Calif.
REFERENCES
Smith,DonaldW.,andHeitmeyer,JohnC.: Lift,Drag,andPitching
MomentofLow+spec=atioWingsatfhibsonicandSupersonic
Speeds- PlaneTriangularWingofAspectRatio2 WithNAC!A0008-63
Section.NACARMA50K20,1951.
Smith,DonaldW.,andHeitmeyer,JohnC.: Lift,Drag,andPitching
MomentofIaw+Aspect-RatioW ngsat SubsonicandSupersonic
Speeds- PlaneTriangularWingofAspectRatio2 WithNACA0005-63
Section.NACARMAXK21, 1%1.
Heitmeyer,JohnC.,andStephenson,JackD.: Lift>Dr% and
PitchingMomentof Lo’w4spect+atioWingsatSubsonicandSupe&
sonicSpeeds– PlaneTriangularWingofAspectRatiokWith
NACA000%3 Section.NACAZ/MA50K24,lgjl.
Phelps,E.Ray,andSmith,WillardG.: Lift,Drag,andPitching
MomentofIow+specHatioWingsatSubsonicandSupersonic
Speeds- TriamgulerWingofAspectRatiok WithNACA0005-63
ThiclmessDistribution,CamberedandTwistedforTrapezoidal
SpanIaadDistribution.NACARMA50mkb,1951.
Heitmeyer,JohnC.,andSmith,WillardG.: Lift,Drag,andPitching
Momentofhw+spec~tio WingsatStisonicandSupersonic
Speeds-PlaneTriangularWingofAspectRatio2 WithNACA000~3
Section.NACAB14A50K24a,1%1.
Smith,WillardG.,andPhelps,E.Ray: Lift,Drag,andPitching
MomentofIhw4spect+RatioWingsat SibsonicandSupersonic
Speeds-TriangularWingofAspectRatio2 WithNACA000%3
ThicknessDistribution,CamberedandTwistedfora Trapezoidal
SpanMad Distribution.NACARMAxK27a,1951.
Reese,DavidE.,andPhelps,E.Ray: Lift,Drag,andPitching
MomentofLow4spec&RatioWingsat SubsonicandSupersonic
Speeds- PlaneTaperedWingofAspectRatio3.1With3-Percenti
Thick,BiconvexSection.NACARMA50K28,1951.
6 NACARMA51H22
8. Hallj Charles’l?.,andHeitmeyer,JohnC.: Lift,Drag,andPitching
MomentofLow-AspectiRatioW ngsatSubsonicandSupersonic
Speeds-TwistedandCmiberedTriangularWingofAspectRatio2
WithNACA0003-63ThicknessDistribution.NACARMA51E01,1951.
9. Heitmeyer,JohnC.: Lift,Drag,andPitchingMomentofbw+lispec+
RatioWingsat EhibsonicandSupersonicSpeeds- PlaneTriangular
WingofAspectRatio4 With3-Percent+l?hick,BiconvexSection.
NACARMA51D30,151.
10.Heitmeyer,JohnC.,andHightower,RonaldC.: Lift,Drag,and
PitchipgMomentofIow+spect+latioWingsatSubsonicandSupe?+
sonicSpeeds- PlaneTriangularWingofAspectRatiokWith
3-Percent+lYxLckRoundedNoseSection.NACARMA5U?’ZU,1951.
11. Heitmeyer, JohnC.: Lift,Drag,andPitchingMomentofLow-Aspec%
RatioWingsatSubsonicandSupersonicSpeeds- PlaneTriangular
WingofAspectRatio3 WithNACA0003-63Section.NACAIWlA51H02,
151.
1.2.Heitmeyer,JohnC.: Lift,Drag,andPitchingMomentofLowAspect+
RatioWingsat subsonicandSupersonicSpeeds– Plane45°Swept-
BackWingofAspectRatio3, TaperRatio0.4With>Percent#Thick
BiconvexSection.NK!ARMA5XH1O,1951.
13. Frick,CharlesW.,andOlson,RobertN.: FlowStudiesinthe
AsymmetricAdjustableNozzleoftheAmes&by &footSupersonic
WindTunnel.NACARMAX24, 1949.
14.Olson,RobertN.,andMead,MerrillH.: AerodynamicStudyofa
Wing+?uselageCombinationEmplo@nga WingSweptBack63°-
EffectivenessofanElevenona LongitudinalControlandthe
EffectsofCaniberandTwistontheMsximumLift#DragRatioat
SupersonicSpeeds.NACARMA50A31a,1950.
15.Herriot,JohnG.: BlockageCorrectionsforThree-Dimensional-Flow
Closed-oat WindTunnels,WithConsiderationof theEffectof
Compressibility.NACARep.995,1950. (FormerlyNACARMAI’B28)
16. Perkins,EdwardW.: ExperimentalInvestigationof theEffectsof
SupportInterferenceontheDragofBodiesofRevolutionat a Mach
Thmberof 1.5. NilCATN2292,1951. (FmnerlyNACARMA81K15)
r
.
-%4 ,.,;.:-.--,,.<*.,i.&---- . . . .. . . . —
,
, ,
* ,
Equation of fuselage rudil
i-= L-’’-Y’J”
All dhensi~s shown h inches
/
~ Moment cenA?r29.66
#
+
-—-
-—
-—
r
-— .— - .— .
t A I I
h )=59.50 ~
Figure 1,- Han view of body.
4
[70
1
Body
R
tD
-4 0 4 8 12 16 20 for M E 0.60
Angle of attack, (X, deg ;
(o) ~ w a
z
Fi@re Z.-7hB variation of the mrafyngmjc Chmoctefjstjes wj?h Ongie of aftack oj VOn”WS ~OCh mmbens.
, 1 , 1
> ,
1
Ii
N
, * , 1
16
I =0.6 0.80 090 Lzo 1.30 /.40 f.53 f. 60 /.70 !2
Ii iliiiii iiiii[iiiiil
H1.O.2’million
0 159mj/lion
1
0 .2 .4 .6 .73 t. o /.2 for # = 0,60
-
Drag coefficient, CD
(b)CDW M
Figure 2.- Ghtinued.
w
.32 I I I I I I /Z/noI I. I I I IPI. I
1
a Body
0.80
R M=O.60
O Q64 minimI
.241 q l.O.?n#llim v II I i I I I RI “ A
I o 1.59~lJrnn I I I
.m
./6
J?
08
.04
0
f &f
w I
/.40 1.53 1.60 f.70 *I
‘W4 O 4 8 IZ K 20 fw M= 0.60
Angie of uttock, K, deg
(c) r&=s u
Figure 2.- Concluded
, ‘1 , ,


Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds : body of revolution

Abstract

Similar works

Full text

Available Versions

NASA Technical Reports Server