Hayes, William C JR

Wiley, Harleth G

English

NASA Technical Reports Server

RESEARCHMEMORANDUM’=
WIND-TUNN’EL INVESTIGATIONSAT LOWANDTRANSONICSPEEDSOF
THEFEASIBILITYOFSELF-ACTUATINGSPOILERSASA
LATERAL-CONTROLDEVICEFORA MISSILE
By HarlethG. Wiley andWilliamC. Hayes,Jr.
LangleyAeronauticalLaboratory
LangleyField,Va.
.
FOR AERONAUTICS
WASHINGTON
JmU=?y 28, 1954
https://ntrs.nasa.gov/search.jsp?R=19930087976 2020-06-17T11:39:40+00:00Z
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TECHLIBRARYKAFB,NM
“.2
.
8
NACARM L53K27
NATIONALADVISORYCOMMITTEEFQR
RESEARCHMEMOFMNIXJM
“=”.Iillllllliillllllllllll;lllillll“--Il. o1442G4
AERONAUTICS
WIND-TUNNELINVESTIGATIONSAT LOWANDTRANSONICSPEEDSOF
TEEFEASIBILITYOFSELF-ACTUATINGSPOILERSAS A
LATERAL-CONTROLDEVICEFORA MISSILE
By HsrlethG.WileyandWillismC. Hayes,Jr.
suMMARY
InvestigationsweremadeintheLangley300MPH7- by 10-footun-
nelandonthetr=sonicbumpoftheLangleyhigh-speed7- by 10-foot
tunnelto determinethefeasibilityof a self-actuatingspoileras a
lateral-controldevicefora missilehavinga 600deltawing. The
lateral-controlcharacteristicsofvariousizesofplainandcwibered
spoilerson a 600deltawingweredeterminedthroughan angle-of-attack
rangeof-4°to 20°atlowspeeds.Theaerodynamicmomentsactingon
twocemberedspoilersweredeterminedthroughan singleof rotation
rangeof 0°to 1800atMachmmibersof about0.6to 1.08.
Resultsindicatedthatsucha systemwill.providecontrolatlow
speedsthroughoutan angle-of-attackrangeof0°to about12°forall
spoilerconfigurationstestedandthatpositiverotationalmomentstill
b= obtsinedthroughouttheangle-of-rotation
— —
of 1.08.
INTROIX.KTION
Simplificationofthecontrolsystem
by eliminatingorreducingthecomplexity
of
of
ra geup to a Machnumber
airplanesandguidedmissiles
thecontrolpowersystem
offerstheadvantagesof lowercostandhigherreMabi13tyoftheair-
frame.Onetypeof controlthatappearspromisingfromthestandpoint
of simplicity,derivesitsmotivepowerfromtheenergyoftheairstresm.
h orderto implementa recentlyproposedmissilecontrolphilosophy
inwhichthemissileseeksthetargetin a constantlycorrectingrolling
. motion(refs.1 and2),a simplifiedlateralcontrolhasbeendevised
whichutilizesaerodynamicforcestopositionspoilersasrequired.The
controlsystemcomprisesa spoilervaneontheupperandlowersurfaces
*
2 NACARML53K27
ofeachwing,withthevanesoriented90°toeachotheron a common l
shaftstichthatone””tendsto spoilthewingflowwhi~ethecompanion
.-
vaneis alinedwiththeairstieam. —
fiordertodeterminethefeasibilityoftheseself-actuating
—
spoilersas a missilelateral-controlsystem,tests”ofseveralaspects
of sucha systemweremadeby theNationalAdvisoryCommitteefor
Aeronautics.
Reportedhereinaretheresultsoftestsat lowspeedsinthe
Langley300MPH7-by lo-footunnelofthe-lateral-controleffective-”
nessof self-actuatingspoilerswithvaryingspoiler .vanechords,span
lengths,andstreamwisecamber.ld.1spoilerstested<onthe600delta_
W@ weremountedwiththespoiler-shaftcenterlinesat37.5percent
wingsemispsmandat82percentwingrootchordandweredesigned ~-
accordingtotherecommendationsf reference3. Tes@ weremadeat
0° angleof sideslipthroughanangle-of-attackrangeof -4.0to about20°.–
Brieftestswerealsomadeof “spoiler-free”actuatingtimesforseveral
caiberedspoilerconfigurations.
Presentedalsoareresultsoftestsmadeonthetransonicbumpof
theLangleyhigh-speed7-by 10-footunnelto determinetheaerodynadc
momentsactingontwoisolatedspoilerconfigurationsthroughan smgle-
of-rotationrangeof0° to 1800.
COEFFICIENTSANDSYMBOIS ‘
Resultsofthetestsof self-actuatirv.spoilercontroleffective-
nesson a 60°deltawingarepresentedasstandardNACAcoefficientsof
forcesandmomentsaboutthestabilityaxesaspresentedinfigure1.
Theorientationf axes
spoilerarereferredis
usedhereinaredefined
liftcoefficient,
dragcoefficient,
pitching-moment
towhichthe‘&rodynsmi;momentson an-isolated
presentedinfigure2. Coeff&cientsandsymbols
asfollows:
Lift
~
Ilraq
qs
Pitchingmomentreferredto 0.25F
coefficient,
qsz
b
--
-.
—
*-
. .
4
—
—
m
v
NACARM L53M!7 3
rolling-momentcoefficient,
Rollingmomentof spoilerandting - Rollingmomentofwingalone
qsb
yawing-momentcoefficient,
Yatingmomentof spoilerandwing- Yawingmomentofwingalone
qm
rotational-momentcoefficientof spoiler,
Rotationaln@mentaboutZ-sxisof spoiler
qsscs
bending-momentcoefficientof spoiler,
[
EBendingmomenteboutspoilerX-sxis)2+
(BendingmomentaboutspoilerY-sxis)1 }
?21/2
wing
mean
root
qSsb~
area, 6.93 Sqft
g
b/2
aero-c chordofwing, S
J
c2dY, 2.31 ft
o
chordofwing,3.46ft
tip chordofwing,O
localwingchord,ft
spanofwing,4.00ft
dists.ncealongwingspan,ft
spoilervanemea, sqft
chordof spoiler(measuredinplaneperpendiculartoZ-axisof
spoiler),ft
spsnof spoiler(measuredalongZ-axisof spoiler),ft
distancealongspoilervanechord,ft
4v
P
q
M
Ma
R
R=
a
8
-d30NFzDm!l?z& NACARM L53K27
free-stresmairvelocity,ft/sec
massdensityofair,slugs/cuft
free-streamdynamicpressure,>V2, lb/sqft .—
Machnumber
averagelocalMach
Reynoldsnuriberof
Reynoldsnuriberof
angleof attackof
K
number .
-.
wingbasedon = ‘“”’
.
—
spoilerbasedon ys
wing,deg —.,= .
angleof spoilerotation(measuredfromplaneo~X- andZ-=”e-so?
spoilerto referencelineof spoiler,positivewhenclockwise),
deg —
MODEISANDAPPARATUS
The600deltawingonwhichthespoilersweremountedforthelow-
speedtestswasthesamewingusedinrefer~ce3 and~adanaspect
ratioof 2.31,a taperratioof0, andwasconstructed_ofa ~/8-inch-
thickflat-steelplatewithbeveledleadingandtrailingedges(fig.3). “
Thedimensionsofthel/8-inch-thickaluminumvinesof spoilers
testedat lowspeedsonthe600deltating,hereinafterreferredto as
spoilers1 to 8,arepresentedinfigure4 andtableI. Eachcomplete
spoilerassemblyconsistedoftwospoilervwes orientedatrightangles
to eachotherandmountedon a comnon3/8-inch-diamete~steelshaftwhich
extendedthroughthewingperpendicularto thewingchordplsme.A com-
pletespoilerasseuiblywasmountedonballbearingsoneachwingsemispan
atthe0.375-semispsmstationandat0.82wingrootchord.(Forthe
control-effectivenesst tsthespoilerswerelockedsothattheupper-
surfacevaneofthespoilerontherightwingsemisp%W= perpendigfl=
totheairstreamwhilethecorrespondingvaneontheleftsemispanwas
paralleltotheairstremn.)Spoilers1 to4 hadplainflatvaneswith
oppositelybeveledlesdingsndtrailingedges_.spoilers5 to 8 were
camberedinordertoutilizeaerodynamicforcestoprovidemorepositive
autorotation(fig.4).
Forlow-speedtestso“factuationtimeforspoilers5, 6,7, and8J”
electricalcontactswereinstalled90°apex%onthewingandwerecon-
nectedto a recordingpotentiometer.Recordswerethusmadeofthe
.
.—
.
—
..
.
=
~
7“
-
—
..
A
d
..
NACARM L53K27 5
;~,,requiredfora 90°rotationofthespoilerfromtheunspoillngor
off positionontheuppersurfaceofthewingto thespoilingor
“on’!position.
ThemodelwastestedonthesinglesupportstrutoftheLangley
300MPH7-by 10-footunneld wesattachedtothetunnelbal.ence
systemformeasurementof aerodymsmicforcesandmoments.A small
fuselagewasusedonthemodelto coverthesupportstrutlinkages.
Thedetailsanddimensionsof spoilers9 end10whichweretested
as isolatedhalf-spoilerson thetrsnsonicbumpintheLangleyhigh-speed
7-by 10-footunnelarepresentedinfigure5 andtableI. These
spoilersconsistedof singlebrassvanesweldedto a l/2-inch-dismeter
steelshaftwhichextendedthrougha rubber-gasketedholeinthecover
plateof thebump.
tricalstrain-g~e
forcesandnmments
Theshaftwa~attachedt= a five-componentelec-
balancemountedbeneaththebumpsurface.Aerodynamic
ofthespoilerwereresilon a calibratedpotentiometer.
TESTSANDcomEcTIoNs
Tests of spoilerlateral-controleffectivenessweremadeinthe
Lmgley300MPH7-by 10-footunnelata dynamicpressureq of
56poundspersquarefoot,correspondingto aMachnuniberof about0.2
anda Reynoldsnuniber,basedon themeanaerodynamicchordof thewing,
of about3 x 106. Thetestsweremadeat anangleof sideslipof0°
andthroughan sngle-of-attackrangeof-4°to about20°. Testsof
spoileractuationtimesweremadeatdynamicpressuresof 25 and56pounds
persqusrefootwiththewingat0° angleof attack.
Correctionsfortunnelblockageandbuoyancywerenegligibleand
werethereforenotappliedto thesedata.
Teststo determinerotational-andbending-momentcharacteristics
of isolatedspoilersweremadeintheLangleyhigh-speed7-by 10-foot
tunnelutilizingthehigh-velocityflowfieldgeneratedoverthecurved
surfaceof a bumplocatedonthetunnelfloor.&picallocalMachnum-
bercontourswiththemodelsremoved,butwithmodelpositionsuper-
imposedonthecharts,areshownin figure6. TheeffectivetestMach
nuniherwasobtainedfromcontourchartssi.num to those *f Wwe 6 W
bs
usingtherelationshipM = # f %& %YS* ReynoldsnumberfortheSa
testsonthetransonicbump,basedonthechordofthespoilervaried
Withlkchnuniberfromabout 0.6X106 to0.8X 106(fig.7). Theiso-
latedspoilermodelsweretestedthroughan angle-of-rotationrange of
0°to 180°.
6 c~ NACARM L53K27
RESULTSANDDISCUSSION
.
-.. ..-
-—:.. .“
Thelow-speedaero@nximic’chsra teri@icsoftheplainwing(fig.8)
werepresentedanddiscussedindetailin.reference3. Thevariationof
rolling-momentandyawing-momentcoefficientswithangk ofattackat
lowspeedsforspoilers1 to 8 me presentedinfi~es 9 and10 and
thevariationsof spoileractuatingtimesarepresentedinfigure11.
Thevariationsof spoilerotational-momentcoefficientswithangleof .—
rotationattransonicspeedsarepresentedin figures12 and13with
thevariationsof spoilerbending-momentcoefficientswithangleof
rotationpresentedin figure14.
Rolling-l@mentCoefficients “_.
.-.
Spoilers 1 to k providedfavorablerolling-momentcoefficients
throughan angle-of-attackrangeof-4°to 12°,withspoilers3 andk,
havingvanespansof 0.15Fand0.25~,respectively,providingthe
greatestrollingeffectiveness(fig.9). (Lateral-controlcharacter-
isticsarepresentedinthispaperforthe“right-roll’-’ conditionwith
theupper-surfacespoilervaneontherightwingorientedperpendicular
to theairstream.Theotheror “left-roll!’condition&esUltsina
negativereflectionofthe“right-roll”condition.)T& cambered ~
spoilerswithsomewhatlessvaneareathanplfinspoilers1 to4 pro-
videdlowerbutstillfavorablerollingmomentsup to ariangleofattack
of about12°(fig.10). Spoiler7 witha vanechordof 0.@b/2anda
spanofO.1’jEhadthehighestrollingeffectivenessofthecsmbered
spoilers.(Althoughspoilers6 and7 h~ generallySMIW vme dimen-
sions,spoiler6, tithgreatercaniberjhadconsiderablyessro~ng .
effectivenessthandidspoiler7. ‘Theincreabedcaniber.ofspoiler6
resultedin increasedfrontalareaofthevaneonthelowersurface
.. ..
—.
.. — --- —
—
.-
—.
.-
thusspoilingtheflowonthelower
theoverallrollingeffectiveness.)
Yawing-Moment
Theyawing-momentcoefficients
surfaceofthewinganddecreasing
-.
Coefficients .— .
-.
forallspoilerstestedweregenerally
unfavorablethroughtheangle-of-attackrangeo?0°to 12°(figs.9 and
lo). Theunfavorableyawing-momenteoei’fiCientsapp=ent~result from
— ——
thepresenceofa spoileronboththeuppersurface
andthelower surfaceoftheleftwing.
SpoilerActuatingTimes
Brieftestsatlowspeedsindicatedthatp@in
and4,tithoppositelybeveledleadingsmdtrailing
oftherightwing
— j .
. ...
—---
spoilers1, 2,3,
edges,wouldnot +
NACARML53K27 7
autorotatesatisfactorily.Spoilers7, 6,7, and8 werethereforebuilt
to incorporatevariousmountsof csniberin ordertoprovidegreater
aerodynamicrotationalmoments.Thetimerequiredfor90°rotationof
thespoilerfromthe“off’!position(uppersurfacevanedinedwith
airstresm)to the“on”(uppervaneperpendicularto airstream),for
spoilers5, 6,7,,and8, atdynsmicpressuresof 25 and56poundsper
squarefoot,ispresentedinfigure11. Ofthefourspoilerstested,
spoiler7 consistentlyrequiredtheleasttimefor90°of rotation.The
timesrequiredfor90°of spoilerotation,areof course,functio~of
aerodynamicrotationalmoment,spoilermomentof inertia,aer@mmic .-
damping,andbearingfriction.Simplecalculationsu ingtherotational-
momentchsracterist’icsof spoiler9 (fig.13)andthecalculatedmo=nt
of inertia,showthatthepredominanteffectson spoilerotational.
timeresultfromaerodynamicrotationalmomentandfrommomentof
inertia.
SpoilerRotational-l@mentCoefficients
Onthebasisof resultsof low-speedtestsof lateral-control
characteristicsandspoilerotationaltimes(figs.9, 10,andM.),
8 spoiler7 wasselectedasthemostfavorableconfigurationa dwas
modifiedto formspoilers9 and10 fordeterminationf isolated-
spoilercharacteristicsattransonicspeeds.(Theisolated-spoiler
. dataareconsideredtobe applicablefora spoilerin thepresenceof
a completewingat 0° angleof attack.)Thevariationsof rotational-
momentcoefficients(momentendingto rotatethespoiler)withsngle
of rotationat severalMachnunibersarepresentedin figure1.2for
isolatedsinglevanesof spoilers9 and10. Negativerotational-moment
coefficientswereobtainedoverpartofthespoilerotationalrange
forbothspoilers9 smd10whenconsideredas single-vanespoilers
(fig.12). Summationsof rotational-momentcoefficientsforcomplete
spoilerconfigurationsforspoilers9 and10 arepresentedinfigure13.
(Thecharacteristicsofthecompletespoilerwereobtainedby algebraic
addition,witha 90°phasedisplacement,oftherotational-momentcoef-
ficientsof similarupper-andlower-surfacevaes.) Positivespoiler
rotational-momentcoefficientswereobtainedforspoilers9 and10
throughouttheangle-of-rotationra geforallMachnwibersinvestigated
(fig.13).
SpoilerBending-MomentCoefficients
Thevariationsofbending-momentcoefficientsCB withangleof
rotationatMachnunibersof 0.6and0.8fora singlevaneof spoiler9
< arepresentedinfigure14. Thebending-momentcoefficientsa presented
areindicativeofthestructuralloadsattherootof thespoilershsft.
“
Fromresultsof teststo
CONCLUSIONS
determinethe
NACARML53K27
feasibilityof self-actuating
spoilersas lateral-controldeviceson a missile,thefollowingconclu-
sionsmsybe drawn.
.—..
1.Favorablerolling-momentcoefficientswereobt~tinedat lowspeeds
oversmangle-of-attackrangeof0°to about12°for~ plsinsxtl
csmberedse~-actuatingspoilersinvestigatedon a thin600deltawing.
_- .- . ,...
2.At lowspeedson a 600deltawing,positiverotationaltendencies
wereobtainedonlyforcsmberedspoilers.AtMachnuiibersup to 1.08,
resultsindicatedthatpositiverotational-moment-coefficientscanbe
obtainedthroughoutansngle-of-rotationraiigeof0°to 1800.
LangleyAeronauticalLaboratoryj
NationalAdvisoryCommitteeforAeronautics,
LangleyField,Vs.,NovemberI-2>1953. ‘-
RlIFER3NCES
1.Curfman,HowardJ.,Jr.,Strass,E.Kurt,
InvestigationsTowsrdSimplificationof
NACARML53121a,1953.
.
.
.-
>
.
. ---
.
andCrane,HsxoldL.:
MLssileControlSystems.
-——
—
2.Gardiner,RobertA.: A ConibinedAerodynamicad GuidanceApproach
fora SimpleHomingSystem.NACARML53110a,1953.
.— T.
—
3.Wiley,HarlethG.,andSolomon,Martin:
..
A Wind-TunnelInvestigation
atlowSpeedsof theAerodynamicCharacteristicsofVariousSpoiler
Configurationson a I%in-600DeltaWing. NACARML52J13,1952.
Colil?mmm%m!a
dz
.
“
NACAFtML53K27 m,. ~
TABLEI.-COCRDllWTl?SFORSPOILERCAMBER
r 1Alldimensionsin inchesunlessotherwisenotedl--
Spoiler5
Y~lx
o
.1
.2
.3
.4
:2
l7
.8
l9
1.0
1.1
1.2
1.3
1.4
1.5
1.6
1.7
1.8
1.9
2.0
2.1
2.2
2.3
2.4
2.5 I
o
0
0
0
00
0
0
0
0
0
.02
l05
.08
.ll
.14
.17
.22
l39
.45
.52
959
.68
.72
Spoiler6
o
.1
l2
l3
.4
:2
l7
.8
:;5
x
o
0
0
0
.01
.04
l10
l17
.30
.42
.56
SPO:8S 7
Ys
o
.1
:;
95
.6
97
.8
l9
1.0
1.1
x
o
0
0
0
0
0
.02
.06
l10
.15
.20
.25
A
Spoilers9
and10
Yslx
o 0
.1 0
.2 0
.3 0
.4 .01
l5 .04
.6 .08
“7 .13
.8 .20
l9 l29
1.0 .38
Lift Po
\
z
t
i
Pitching mmenf/
.
.
x
\
Wind
‘e’”
)’
z
Figure 1.- System of fitabilltyaxes. Positive values of forces,moments,
and amglee are Indicatedby arrows.
I
,, 1 ,, .,,
NACARM L53K27 11
.
.
z
+
@ofotionu/moment
Y I
\
1
\
I BendingmomentUboutx- OXis
\, +’
‘ J
__Spoiler reference >-4-’
.r~” + TJ‘=
& “ ‘.
Wind
‘(x
I Y
Bendingmoment
obout Y-uxis
i?
Figure2.- Systemof spoileraxes. (Positivedirectionofmoments
indicatedbyarrows.)
.-
.-
I I I
Fignre 3.-
1 Roof 0015
Moximm 0045
Sketch of 600delta wing showing location of spoilers. (&Ll
dlmens~onsme h Inches unless otherwisenoted.)
1-
ro
.
,
,,
r--%---i
r
[ Typ/col hSfOhYt/On)
L I I I
Spohr 2
Y==@=- ‘;”
frypkd spoilerm= secmd
Epoilem 1,2,3,4)
SpoiJer 4
Sphiler6 Spoiler7 Spoiler 8
(Typical spoiler vane sdbd
(Spoilers 5, 6)7,8)
Figure k.- Details of plain and camkred spoilem tested on 60° thin
delta wing. (Coordinatesof cemilmredspoilersare presented in
table 1. Al-1dimensionsin inches unless otherwisespecified.)
14 NACARM L53K27
r
A 44
-!
T 4
Spoiler 9
Spoiler @
reference
‘d
’30°
Sectio~
Spoiler10
A-A
Figure5.-Detailsofspoilerconfigurationstestedonbansonlc bump.
(CoordinatespresentedintableI. AlldimensionsininchesWless
otherwisespecified.)
.
.
l
.
.
—
.8
0
8
o
M. I
MI
——— —
I
L-
2
‘.78’0’2
8
6
4
2
.&?~
-.8z.-
——— .0 ——.t0.?4 6 8 10 12
Centerlhe of spoiler vane ——— Boudory-@er th~kmss
L
.—— __ L -.. . ———
2 4 68
Stotion on bump , in
Figure 6.- ~iCd. Mach
10 12
8
Ml
#l!&
K25
2
.— ——
number centours over
of model location.
2 4 b 10 Ii?
Station on bump, in8
transonic bump in region
~
‘k!
--J
G
,.8 X /0”
&——
.6 .8
Much /Vum&tY, M
L2
Figure 7.- Variation of Reynolds numberwith Mach number for spoilers
tested on the trsnsdc bump.
I!*
NACARM L53K27 17
.
.
0,
.
./
o
c.
-./
.8
.6
# C*
.2
I I
I 1 ,I I
lji.i LJ---kTiiii o
Ut
-H’ I I I I I I I I I I 1 1
72 0 .2 # .6 .8 10 L2
c“
Figure8.- Theaerodynamiccharacteristicsofa plain600deltawingwith
anaspectratioof2.31,taperratioofO, andconstant-thicknessair-
foilsection.
18 NACARM L53K27
Spoiler &o /,
0 2 ml
A
I i
3’
v 4 1
—
“.
....
->-
.
—
-4 0
Figure9.- Lateral-control
ona 600deltawing. M
48
C@tt
characteristics-
/2 /6 20
.
.
ofplainspoilersinstalled
= 0.2. (Datapresentedfor“right-roll.”
condition.Flaggedsymbolsindicatechecktests.)
&~
NACARM L33K27 19
.0/
c~ o
-.0/
.03
.02
cl .0/
o
-.0/
.
.
-4 04 8 /2 16 20
Figure10.- Lateral-controlcharacteristicsof camberedspoilersinstalled
ona 600deltawing.M . 0.2. (Datapresentedfor“right-roll”
condition.)
20
./6
./2
.08
.04
6
7
8
NACARM L53K27
I
m.III)
El----
---
-.
0
20 30
%
Figure11.- Variationoftimeof90°
dynamicpressure
600deltawing.
(
--— .,
u
50 60
ofrotationfr~ “off~’yositionwith
forcamberedspoilerstestedatlowspeedsona
~ql~z>-:.~
.
.
-i
@(2 ,2
0
-.2
OZW 4060&U /00 /m 140 /60 /80
8
(a) Spoiler9.
Figure 12.- Variation of rotational-momentcoefficientwith angle of
spoiler rotation for spoilersmounted on traneonlcbump.
l
I
. .-
0
04
Cff
0.2
u
-.2
(b) 61JoihZ 10.
Figure L?.- Concluded.
I I s .
.3
.2
.1
0
Cff
.3
.2
,/
o
02040fm 80 I(W /20 140 160 AW
8
Figure 13.- Summationof the variation of rotational-momentcoefficient
with anfjleof rotation at trausonic fipeedafor spoilers consideredto
be mouuted on upper wd lower surfaces of wing.
I.8
.6
.4
0.2
0
I , I Id I I I I A. A I I . , T I
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Figure 14.- Variation
s
. rotation for
,,
60 80 K?O /20 /40 /60 f80
of bending-mcnnentcoefficientwith engle of
spoilermounted on transonicbump.
*’* f ,
1 1


Wind-tunnel investigation at low and transonic speeds of the feasibility of self-actuating spoilers as a lateral-control device for a missile

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