Document
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NACA
ESEA CH MEMO ANDUM
TIIEWEl'ICAL AIm EXPLRDtENTAL DATA FOR A NUHB.l!:R OF NACA 6A-SEPIES AIP~OIL SZCTIONS "" .
By .
Laurence K. Loftin, J r.
Lane16Y Memorial Aeronautical Laboratory La.n[dcy Field , Va: ,-- .. - .. ~" • '; , • .It...... I " ,....-
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AV-V
NA llONAl ADVISORY COMMITTEE
FOR AERONAUTICS .
• WASHINGTON
DEC 6
ITA CA EM No. L6J Ol NA TI O NAL AJJVI SO RY CO MMITl'EE FOR AERON A UTIC S RESEAR CH MEMOR ANDUM TBEORET I CP.L An D ElCPEPD1EN'l'l' .L DNlA FOR A NUMBF.R OF NACA 6A -SERIES AIRFO IL SE CTI ONS By L aurence K. L oft in, J r .
The ITACA 611--serios airfoil sections were designed to oliminat e the trailing - ede;e cusp '"hicl is chl.'J:'acteristic of the Hf.CA 6- series sections . Theoretical d.ata are prosented for r!ACA 6i',- series basic th i ckness forms havinG the position of ninim~m pressure at 30 -, 40 -, and 50 - percent chord and with thic!mess ratios varying fro m 6 percent to 15 percent . Also prese ~ te~ are data for a mean l i ne designed to lllaint~n GtrE:.ight sides on the cambered. sections .
The experimental resu .l ts of a t~"o - climGns i o n al vr in d- tunne l investigation of the cerodyncmic ch~actertstics of five N.CA 64A -s e ries airfoil sections and two N CA 63A- series airfoi l sections are precented . An enalysis of these results , >Thich irei'e obtained at 6, 6, 6, Reyno l d.s numbers of 3 X 10 6 x 1 0 and 9 x 1 0 indicates that the sect i on mininr.nn drag and mro:imuiD. l ift ctaracteristics of camp~'ab l e NACA 6- series and 6l~ - series airfoi l sectio n s are essen - tial l y the sane . The quarter - chord pitching -moment coefficients and angles of zero l ift of NAC!, 6; ~ - ser i es airfoi l sections are sl ight l y more nogative than those of correspond.ing NA CA 6- series airfoi l sections . The position of the aerodynamic center an d t he li ft - curYe s l ope of smooth N l..CA 6A ·· series aix'foi l sect i ons appear to b e essentially· i n d.epend.ent of airfoil thickness ratio in contra s t to the tren t'is hown by Nl.CA 6- series sectio n s . The addi ticm of standard l eading - edge roughness cau.ses the li ft - curve slope of the ne v er sections to decrea8e ,,,i th increasing airfoi l th i cknes s rat io.
D fl'RODUC'.::'ION Con s i derab l e interest is be i ng shOi-m in airfo il sectio n s havipg smal l thickness rat i oG be c ause of' their h i @l cr i t ic al Ma. ch n um b ers .
Th e NACA 6 - serios Dirfo il s oct i on:..> of smaJ.1 t h ickness h ave re l at i ve ly hi gh cr i tical ~,bch nUI"lbers , b ut ha.ve tho disadvantage of being very 2 NACA RM No. L6JOI thin neBX the t:cailiDg e~o , particl1larly "Thon the sections consid.ered have tho position of minimum li resslJre viell forward on the basic thickness fo:cm. ThE'! ' I;hin t: c ailing-edce portIons lea(l c o" di f f1cultien in structural decign ~d fabrication .
In oru.er to overcom.e the difficultiea, the t:cailing-edt:;e cusp has be en removed. from a llvmber of NACA 6-8erios basic thiclmess i'Or'"lllS and the sides of the atrfo:i.l sections made straiGht f:r' om approxim.ate l y SO - percent cho!'d to tho trailiI1..g edGe . These n8H' sections ' cre deeignaccd NACA 6iI.-sories o.i:-cfoil sections . A
special meen line d6sign.ated tho a = 0 .8 (llloclifie6.) mean line
has also been d.esigned. to maintain st:caight sllies on the cambered.
oec ti ons .
This pareX' pl~esents theoretical pressure-distribution data and o:~dinate8 f01' NACA 6A-series basic thickness forms covering a range of thickness l'ation extendins from 6 to 1 5 percont and. a ranee of positions of minim1.,UD. pressl'.re extendine fro!ll 30-percent to 50 - percent chor(1.
The aerodynE'Jllic characteristics 01' 8even NACA 6A-scries airfoil sections as dE.. termined. in the Lengley two-dimensional lOv-T - tur bul ence procsu.re tunnel are also presented. . 'Ilhese d.ata a:ce analyzed. and c o m:,}er od ,- Tith s imilur' d.nta for NAC A 6- s er j. es ai rfo i l sec t ion s of comp8r3.bl e t_licl~ness and dcoign l ii't coe ff icien t. .
• , 6' '" • " - . ... .. . " ,- ~. '. " " ' . " .: '.' . .; - _ . • • . ". •• ~ •.• : .- ,,' ,m' .' , .. "': :'" COEFFICIENTS AND STIJIBOLS Cd section dr8.6 coefficient 0dmin minimum secti on drag coefficient c 7. section lift 0 0efficient design section Uft coefficient qi c7,. maximvm section 11ft co efficient mo;x: C . c. sect 1 on pi tchlnc;-moment coefficient about aerodynamic center ma ~/4 section pitchinE,-moment coefficient about qUaYter -ch ord point I I'JACA RM No . L6JOl (!,o section angle of' attack ~ section angle of attack correspon0ing to design lift coefficient ctq d~ section lif t-curve slope V free-stream velocity v local velocity 6v increment of local velocity 6v increment of local velocity caused by ac.di tional type of loa.d a distribution resultant pressll.rc coefficient; difference betw'een l ocal upper-surface and l Oir -surf ace pressure coefficients R Reynolds r..umber c airfoil chord lellb~h x distance alo chord from the leading edge y distance perp0?d~ClUar to chord yc mean-line ordinate a mean-line deSignation , fraction of chord from l eading edge over llhich design load is uniform ;f oirfoil d~sie;n parameter ( reference 1) THEOREl'ICP.r, CHA11ACTERISTICS OF AI.RFOILS Desi~t.!2!.! ' - The system used for designating the new airfoil ..
sections 1s the same as tha-lj employed for the NACA 6- serie8 sectio!'1..8 (re ference 1) exce::;>t that the capital l etter flAil is substituted for the dash "Thich appoars botHcen the digit denoting the position of mi~um preSSlITe and that denoting the ideal li f~ coefficient .
For example, the NACA E~ -212 ?ccomes tho NACA 64 /121 2 when the cusp is removed from tho trailill£ odgo. In th e abconce of any further modification to the deai~11ation, the cambered airfoils are to be consi , iered. as having the a:::: 0 .8 (modified.) mea.n. line.
NACA PJv1 No . L6JOl ] . ~'3i_c thickne . ss form.Q . - The theoretical methods by .Thich the basic thickess forms of the NACA 6-series family of ail'foi l sections I,rere derived so as to have pressure distributions of a specified type are described in reference 1. The process of removing the trail i ne - ecige cusp ,'las accomplished by increasing the value of the airfoi l design parameter \j: ( reference 1) corresponding to the rear portion of the airfoil until the airfo::'l ordinates formed a straight l ine from a'pproximately 80-percent chord to the trailing edge . Once the fin a l. form of the -..!,' curves w'as establiohed , the now pressure cl_istribut5 . ons Gor-responc1.ing to the modified thickness forms were calculatod by the usual methods described in reference 1.
it comparison of the tbeoreticru l:rr'essure distributions of an NACA 6~-012 airfoi l section and an NACA 64 A012 airfoil section l ( fig . 1) indicates that remo v ing the trailing-edge cusp has but little effect upon the velocities around the section. A slight "-'ed1l.ction of the peak negative prescure and flatter pressure gradient over the ronTard and rear portions of the airfoil s ection seem to be the principal effects . The tbeoretical crucvlations also indicate the presenc~ of a trailing-eclEe stagnation point caused by the finite trdling-edge angle of the NACA 6A-series sections.
This stagnation point is , of course, never reali zed experimentally.
Ordinates and theoretical pressure-distribution data for IiiACA 6..\-series basic thickness forms having the position of mir~um pressure at 30-, 40 -, and 50-percent chord are presented in fig1ll ' es 2 to 16 for a:.i.:r'foH th i ckness ratios of 6, 8, 10, 12, fu'J.d 15 percent . If inte:rm.ediate thickness ::catios involving a cha.nge in thickness of not more than 1 to 2 percent rone desired, the ordinates of the basic thickp..6sS forms m8JT be scaled linearly .rithout seriously altering the gradients of the theoretical pressure distribution .
. M~'§'!Lline. - In oj.~d.er that the addition of cmber not change tho press~lre gradients over '0he basic thiclmess form , a mean line shoul~ be used which causes uniform load. to be carried from the leading edge to a point at least as far back as the position of min.i.:m:um pressure on the basic thidmess form . The usual practice
is to camber NACA 6-se1'ieo airfoil sections vri th the a = 1.0 type
of mean l i11e because this mean line appears to be best for high ,.
max:iJ:n.um lift coefficients a.Tld , contrary to theoTetj.cal predictions, does not cause excessive quarter - chord pitching-moment coefficients .
The a = 1.0 typo mean line was not considered desirable , ho,fever, for the NACA 6ft- series basic thickness forms because the sv.rfa c es of the cambered airfoil sections vTould be cur v ed near the trailing edge . The type of mean line best suited for maintaining (~ I [ NA CA RM No . L6JOI straight s1des on these newer sections wov~d be one that is pe r fe ct l y straight £'rom 80-percent cho!'d to the trai l ing ed.?;e . Su ch a caniber
l ine c ould be obta i ned by modif;ring an a = 0- . 7 mean l ine . C ons i dera -
ti on of the effect of mean-line load_ing upon the maximum l if t coefficient indicated, ho,'rever , that a mean l ine having a uniform 10aU distribution as far back al ong the chord as possi bl e was desirab le.
It was f01md , that the a = 0.8 t~rpe mean line c ould b e made straight
from approximate l y 85-percen-c chord to the trai l ing edge wi thout causing a sharp bre1Jk in the mean l ine and i,d_th very l ittle curvature betw-een 80 - percent and 85 - percent cho:c'd. . The aerodynamic advantages of using this InGan l ine in preference to one having uniform load to 70-percent chord were considered to be more important than the
slight curvature existing in the modifie~ a = 0 . 8 mean line . Fo r
this reason , Dll canwered NACA 6A - series airfoi l sect i ons have employed the a = 0 . 8 ( modified) mean l ine .
The ordi..Tlates and load-distribution data corresponding to a design lift coefficient of 1.0 are presented in fi.:;uro 17 for the
a = 0 . 8 ( modified) mean lino. The ordinatos of' a neaD. line having
any arbitrary deeign lift coeffiCient m~ be obtained simply by multiplying the ordina-cos prosented by the desired design lift coeffici~nt .
Cambered airfoils . - The method used for carabel'i ng the basic thickness distributions of figures 2 to 16 'ivith the mean line of figul'e 17 is described and discussed in references 1 and 2. It consists essentially of 10\{ing out the ordinates of the basic thickness forms normel to the mean line at corresponding stations .
A discussion of the method effij:l l oyed for combining the theorotical press'..U'e-distrib'-ltion data , pr.-esented in figu.res 2 to 17 for the mean line and basic thickness distribution , to give the approximate theoretical preSS1-1..Te distribution about a cambered or symmetrical airfoi l section at aD~ l ift coefficient is given in roference 1 .
APP ..A.RATUS ,'\J.I.Jl) TESTS 'Hind t-unne1. - All the tests described in this report .rere conducted in the La.ncloy hro-dime-nsional low - turbulence prOSSVTe tlUIDel. The test section of this tunne l IDBasures 3 feet by 7 . 5 feet .
The models compl etely spanned the 3-foot dimension vrith the gaps • between tho model and tvnnel '-Talls sealed to pl ' event air l eakage.
Lift meaE'urernents were made by taking the difference bet\voen the pressure reaction upon the floor ~Tld ceiling of the tunnel; drag results vlere obtained by the '-lake-survey method and. pitching moments were determined. \-71 th a torque balance . A more complete description of the tun11el and the method of o btaining a.."1d r e ducing the data are contained in reference 1.
r------~-- . ..._ - NACA RM No. L6JOl Models ._ - The seven airfoil sections for which the experimental aerodynamic characteristics were obtained are: 63AOIO 63A210 64AOIO 64J1210 e.t A21:; 6!J.A410 The models representing the airfoil sections I'Tere of 24-inch ch ord. and were conctructed of laminated mahogany _ The models were painted with lacquer and then saTl.ded uith number 400 carborundum p a::;>e r until ae:,:,odynamically smooth su.rf aces '\-Tere obtained . The ordinates of the models tested are presented in table 1.
Tests,- The tests of each smooth airfoil section consisted of measurements of the lift, drag, and qua:cter - chord pi tching- 6.
moment coef f. icients at ~eynolds numbers of 3, 6, and 9 x 10 In addition, the lift a.Tl.d drag characteristics of each section were determined at a Reynolds nUJ'!lber of 6 x 10 "lith sta..'"1dard roughness applied to the leadine ed ge o~ the model. Tho standard rougrJless employed on these 24-inch - chorC: models consisted of C. Oll - inc.J.'!.- diameter carborundum e;rains s::?!,eud over a sur:i:'ace length of 8 percent of the chord back from the leading edge on the upper and lOYTer surfaces. The grains "toTere thinly spread to cover from 5 to 10 percent of this area. In an effort to obtain some idea of the effectiveness of the airfoil sections when equipped ,nth trailing - edge high -l ift devices, each section was fitted w · ith a simulated split flap deflected 60 • Lift measurements were made using tho split. flap at a Reynolds number of 6 X 10 w·ith the airfoil leading edge both smooth and rough .
RESULTS The results obtained from tests of t' e seven airfoi l sections are present e d in t he f orm of standard aerodynemic coefficients representin g th e li f t, drne, and qua.rter-chord pitching -m oment • characteristics of the airfoil sections in figures 18 to 24 . The calculated. position of the ae:!:'odynamic center and. the va:dation of the pitching-momen t coe f fici e nt with lift coefficient about this point ai.~e ruso included in these data. The inflt~ence of the tlUlllel l I NACA RM No. L6JOI 7 boundaries has be en removed from all the aerodynamic data by :means of the folloyring equations (d eveloped in refere nc e 1): o . 990cd t
cd =
q 0 . 973c 2'
=
, O. 95 1 c
=
c / m mc a 1.0150.'
=
.There the primed. quanti ties denote the mea sured coefficients .
DISCUSSION Although tl:.e 8m.ovnt of systematic aerodynamic data presented for NACA 6A - series airfoil sections is not large, it i s enough to indicate the relative morits of the NACA 6A - series Birroil sections as compar ed with the NACA 6 - series sections . The variation of the important aerodynamic characteristil;s of the five NACA 64A-·series airfoils ,vi th the pertinent geometrical parameters of the airfoils is shO"tm in f i gvres 25 to 31 , togethor vTith comparable data for NACA 64 - series ail~foils . The curves shown in fi rres 25 to 31 are for the NACA 64 - series airfoil sections and are taken from the faired data. of reference 1. The experimental points which appear on those figures represent the results obtained for the NACA 64A- series a'rfoil sections in the present investigation . S inc e only two NACA 63A-series sections were tested , comparativo results are not presented for them . The effect of removing the cusp fra.il1 the NACA 63-series sections is about the same us tha~ of removing the cu s p from the NACA 64-series sections.
The compare.tive date. shovring the effects upo n the aerodJrnamic characteristics of removing the trailing-edge CUBp from NACA 6-series airfoi l sections should be ap:plied with caution i f the cusp removal is affected in some maTLTler other than that indicated . earlicr in this paper . For 6 xaLlple, i f the cusp should be removed from a cambered airfoil by means of a straight-line fairing of the airf oil surfaces, the amount of camber lvc uld be dec:ceased ncar the trai ling edge . Naturally , the effect upon the aerodynamic characteristics of removing the cusp in such a manner would not be the same as in di c ated. by the comparative results presented for NACA 6- series and 6A -s cries airfoils .
J
8 NACA RM N o. L6JOl Dr.§B . - The vllrlatio n of section minimum drag c oefficient wit h airfo il th:Lclmess ratio at a Re:rnolds numbe:,:, of 6 X 1 0 is shown in figuI'e 25 for NACA 64 - 3er1e8 and NACA 64 · .'\.-series airfoil sections of various cambers , both smooth and. ,.;ith standard 1eacling-ed~e roughness . As ,.,i th the NACA 64 - se1'ie8 sections ( reference 1 ), the minimum drag coefficients of the NACA 64A-series sections shoyT no consi . stent variation vli th camber . Ccmparison of tile data of figure 25 :'nQicates thc.t ). 'em D ving the cuop from the t.railing edge has no aprxreciable effect upon the minimum drag coefficients of the airfoi l s , either smooth or with standard leading - ed€e roughness .
6 6 I nc reasing the Reynolds numbeX' from 3 x 10 to 9 x 10 has about the SaIll0 effect upon the miniml.lJ!l drug coefficient of NACA 64f - ser:Les airfoils ( fi 3s . 18 to 24) as that indicated in reference 1 for the NACA G4-seriee ai::1.'foils .
Some differences exist in the drac coefficients of !rACA 64 - and 64A-series a.irfoils out3ide the 10"iT-d.:.'ag raI1€e of lift coefficients but these differonces are small and do not shor any consistent trands ( figs . 18 to 24 and refer e nce 1 ) .
~~1~ .- The section anc l e of z ero lift as a ftmction of thickness ratio ls shovm in figtrre 26 for NACA 61~ - and. 6hA - series airfoi l suctions of' various cambers . These res"Jlts show that the engle of zero l ift is near l y inde:gendent of thicY.ness ancl is primerily dopendent upon the amount of camber for a particulDr type of meen line . Theo:retica~ calculr. . t.ions using the mo an line datu of fi~'Ul"o 17 and reference 1 indicate that the airfoils using
the a = 0 . 8 ( modified) m0an l ine should have an.:;lo13 of zero lift
less negative than i- mul d be o btainod if on a = 1. 0 type mean
line wer e used . Actual l y tho reverse appears to be the case due
mai nl y to the fact that airfoils usin G the a = 1. 0 type of mean
line have aneles of zero l if' "'hich 81~C only about 74 percont of their theoretical value ( re f orcmce 1 ), and t!le a = 0.8 (modi fIed.)
meOJ.J. line s have an e; 1 6'3 of zer o li f t llll '~ el' -r.:.t.B.n in!lic£l!i7.ed bJ theor y .
The mee.strred l ift - CUl~ve slopes cor-rosponding to tho NACA 64 - series and RACA 64A - series atrfoils of various cambers are presented in fig n'o 27 as a fun::tion of airfoil thickness ratio . No consistent variatio n of lift - cUY've slcpe with camber or Be- nolda nUI!lber is shO'im ,by oi tllOr tYl)O of airfoil . An incrc ~ o in t i~ ail:i.n c -odi2o 8.Il.[, l v y:i.' odu co ,l ·o J r(; ]l o .... -aJ. of t h o G '. ~ er tonds to :;.' od.~'..ce .thE; li f t '-c'.,U've slop e by 8..1J. amount 1'1hich increa s es i" ith airfoi l thicknoss ( s ee referoncos 3 and L ~), but it apJ16al':'S that , for tho 61\-801 ' 108 airfoils , this decrense in l ift - cu:cye slope i s just cnoU3h to equal the no:L"ln l increuse in lift - curve slope caused by airfoil thich.-ness because the presont data fo.(' the
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- - - ----~--------~~-----~- -- --- NA CA RM No . 16JOl 9 6A - sectiolls show practical l y no yarj_ation \ori th thiclmess . T he v al ue of the l ift - curve slope for smooth NACA 64A- series airf o il sectio n s is 'Tery cl ose to that predicted from th i n airfail theary ( 2 rc per radian or O .li O !;ler degree) . 1rlith sta."1dard l eading - edge roughness , remav i ng the trai l ing - edge cusp callses the l ift - curve slope to' decrease quite rapidly vrith increasing airfoil thickness ratio .
The variatian af the sect i an maximv.m. l ift coefficient "nth airfoil thickness ratio 8..."'11 camber at a Reyna l ds m:rrn.ber af 6 X 10 is shown in figure 28 far NACA 64-series and NACA 64A - scries airfa il sectians vrl th end vri thaut standard leadine::-edge roughness and simu l ated split flaps deflected 600' . A comparisan af these data indicates that the character of the variatian of mQXimum liit coefficient vl ith airfoi l thickness ratio ond camber is practica.l l y the same far the NACA 64 - series ancl Nl\.CA 64A- series airfoil sectio n s .
The magnitude af the maximum lift coeffi , ient appoars to be slight l y less for the plain NACA 64A-series airfoils and slightly higher far the NACA 64A- series airfoils vrith split flaps t han carresponding values faT the NACA 64- serie8 air:1:'oils . These differences are small , hawever , and for engineGring applications , the ma.ximum lift cha.racteristics af IJACA 6~- - serie8 and 64A - 80rie8 air:'oil sect:lans of camparable thickness anQ design lift caefficient ~ be considered a.s practically the same .
A comparisan of the maximum lift data f or NACA 64A-series airfoil sections, with similar data for NACA 64 - series airfoil sections , presented in fiGtrrcs 18 to 24 , indicates that the scale - effect chm'actelAistics of the tw'o types af section are essentially the same for the range of Reynolds number from 3 x 1 0 6.
to 9 x 10 Pitching mament .- Thin - airfoi l theory lJravides a means for ce~culating the theoretical quarter - chord pitching -moment caefficients of airfail sections having various amovnts ruLd types of camber .
Calculatians were made accordinti to these me t hods for airfoils
employing the a = 1 . 0 and a = 0.8 ( modified) moan lines using
the theoretical meaD- line data presented in figure 1 7 and in reference 1. The results of these calculations indicate that the quarter - chord pitching-moment coefficients af the NACA 64A- series airfoil sections , employing tl!e a = 0 . 8 (modified) mean line , should be only abaut 87 percont of those for the NACA 64-seri6s
airfa il sections \on th the a = 1 . 0 mean line . The experimental
rela.tionship bet",,-een the CJ.uartel~ - chord pitching -moment coefficient end airfoil thickness ratio and camber , ShOinl in f:te;ure 29 , discloses that the pl ain NACA 6hA-aerios ru.rfoil.s ht.. e pitching -mon.ept coe ffic ients which are s l ie.ht l y more negative than those for the :plain NACA 64 - series airfoi l s . The increase in the magnitude of the pitch i ng - ma ment
~_
_ J
10 NACA RM No. L6JOl coefficient of NACA 64A-series airfoils as conpared with NACA 61~ series airfoils becom es grenter when th~ airfoils Ql'e eCluipped c wi th simulated split flaps deflected 60 • A compa"J:'ison of the theoretical and. measured pi tclling-moment coefficients i s Sh01ID in fiE:ure 30 for NACt. 6 2~ -seri es a.Tld 64A-series airfoil sections.
Those comparative data indicate that the HACA 6l~A-se ries oections much mo~~e nearly realize their theor6tical moment coe ffici ents than do tho 6l~-scrIos airfoil sections . Sim:i.lar trends have been
shown to result ",hen meen lines such as the a = 0.5 type ru:e
employed wi th NAC. ,.r~ 6··serie3 airfoils ( l'efore nce 1) .
Aerodynamic center . - From the Cluorter-chord pitching -moment data , the posit ion of the aerodynmnic center, a.Tl d t:t.e variation of the moment coe fficient about this point with li ft coefficient, wore calcula ted for each of the sevcm D.irfoi18 teste d . The variation of the ch ordwise pocition of the aoro~amic 0enter "lith airfoil thickness ratio i s shown in figure 31 fo r the NACA 64-series and. 64A-series aiL'foil sections. The data pre se nted for the NACA 64-serie8 airfoils aro for Qll cambers and., in accordance "nth these resuJ.ts, the position of the &erodynamic cen te r shows no consistent variation "lith can ibel~ for t he NACA 64A- series airfoils . The dnta of f'iGl.1rCS 18 and 24 sho,\v tha t variations in the Reynold.s numbor h ave no co nsistent effect upon the chordwj.se position of tho aeroc1ynmnic c ente r.
Perfect fluHt theory indica t e s that the posiM.on of t ho aerodynumic center sho'Lud move roarwnrd with increasing airfoil thickness and the experimental results for the NACA 61.~-series airfoil sections follOl this trend. Tho data of reference 5 shm-, impor tant v fO:r'lv8:rd movem e nts of the aerodynam:tc centor with inc reas ing trailing- edge angle for a given airfoil thickness ratio . The results obtained for the NACA 24 - , 44 -, anti 230-series aii:foi l sections (referdnoe 1) reveal that the effect of increa s ing trai ling-e dge ancle predominateG over the effect of increaeing thickness bec ause the position of
the aerodynamic center moves forward 1.n th increa8ing thickness ratio
for ther:e airfoil seetions . For the NACA 6L~A- ser ie s airfoils ( fig . 3 1) the aerodynamic conte :: is slightly behind the CluaJ..'ter- chord point and does not appeel" to vary \- ri th incro 2.s i1"-8 thi c kness.
These reS'lJlts suggest that the oIJPosite ef::ects of increa s in g thickness and trailing-edge angle counterbalance eecll o ther for these air fo il sections .
CONCLU S IONS From a tvro-dimensional vind.- tun.Tlel inyest1ga"c10n of the aerodynamic char ac toristics of five NACA 64A-series and two NACA 63P--series air f oi l sectj . ons the fo lloviin g con c lu s ions based N A CA RM No. L6JO I 11 6 6 upon dat a ob tai n ed at Reyno l d~ ntunbers of 3 x 10 , 6 x 10 , an d 9 X 1 0 may be drawn: 1 . The sectio n minimum drag and maximum l ift coe ffici e nts of correspo n ding NA C A 6- series and 6A - se ries airfoi l sections are essentially the same .
2. The l ift - curve sl opes of smooth NACA &-1 - 8er ie s airfoi l seceions appear to be essent.ial l y independent of airfoi l thi c kn e ss ratio , in con t ra st to t he trends shovm by NACA 6- sories airfo il sect i ons . The addi tion of standard l eading - edge roughness causes the l ift - curve slope to decrease with increasing airfoi l t h ick n ess ratio for NACA 6A - serie o airfoil sections .
3. The sectio n angles of zero lift of NACA 6A - series ai rfo il sections are sli gh tl y mo re ne ga tive than th o se of comparabl e NACA 6- series airfoil se ction s .
l! _. The se e- tion (~ uo.rte :: - chord pitchiIlG - moment coef ficients of NACA 6A - series airfoil sec t ions are sl ieh t ly mOTe nega t ive than those of comparabl e NACA 6- series airfoil sections . The position of the aer odynamic cen t er i s essential l y inde p endent of airfoi l thickness r a tio for NACA 6A - se r ies air f oi l secti o ns .
L angl ey Mem o rial Ae r onautical Labornt~y Nati onBl Ad.visory C01ll!l1:i ttee f or A er o nautics Langley Fi e ld , Va. , / ' Laurence K. Loftin , Jr.
Aeronautical Engineer
Ap p roved : ", I
'0 r; :':Z n '/ /[~ -C l ' //. d /i , Clinton H. Dearborn Chief of Full - Scale Research Divisi on bV T NACA RM No. L6JOI 1. Abbott, Ira H., von DoeI1.hoff, Albert E., end Stivers , Louis S., Jr.: Summary of Airfoil Data. NAGA ACE No. L5C05, 1945.
2 . Jacobs, Eastman N., Ward, Kenneth E., and Pinkerton, Robert M.: The Character~stics of 78 Related Airfoi l Sections from Tests in the Variable-Density vlind Tunnel. NACA Rep. No. 460, 1933.
3. Purser, Pa1J~ E . .. and I'<1cKee, J·ohn W.: Hind-Tunnel In vestigatio n of 0. Plain Ailel~On vTith Thickened. and Beveled. Trailing Edges on a Ta:pered LOvT-Drag 1.Jing . NACA ACR, Jan. 1943.
L~. Jones, Robert T . , and Ames, Hilton B., J r .: Hind-Tunnel Investi- Gation of Contr o l- Surface Characteristics. V - The Use of a Beveled Trailing Edse to Reduce the Hine;e Homent of a Control 81ll'face . NACA ArIR, Narch 1942.
5. P1.1!'ser , Pa1J~ E., a.lld John son , Harold S. : Effects of Trailing-Edge Modifications on Pitching-Moment Characteristics of Airfoils.
NACA CB No . L4~( 30 , 19)+4.
• •••••• • • NACA RM No. L6JOl •• • • •• • •• T AB LE I '. .
ORD I NA 'lES OF lIA CA 6 A-SE RI ES AIRF OI L SEC TI ON •• • • •• • •• • • . ....
• •• • •• •• • •••••• • • NACA 63A010 N AC A 63 A2 10 ~tatl o n8 and ordin a tes g Iven 10 percent of airfoIl c h o~ lo w er S urface Up p er Surface Upp er Surt'ace Lo w er Surface Ordinate Station Ordinate Ordinate Stati on Ordin at e Statlon S tati on 0 0 0 0 0 0 0 . 86 8 - .7 56 .423 .577 .8 16 - .816 · 5 ·5 .664 .8 6 - ·900 1.°l8 - 1.1 25 1J~6 1J ~ - i J~6 4 l.p
l:H
1.~1 1.3~ 2. 4 2. 16 - 1.52 2 10 1.9 2 . 5 2 · 5
- m
-2 .
un 5·0
5· 0 -2·m -2.
h f4 U ~ 1 :B!
7 · 5 - 2 . 9 ~ 7 · 5 2 . 9 ~ 10 .137 10 10 - 3. 3 3 3. 3 - 2. 7~ Z · 86 - 3.16
UF 1 . 869 15·131
5O 15 5O 1 .882 5. 328 20 .u 8 :: e-4 20 . 00 20 . 00 l"4 - 3 ~ 2 . 89ij 6 25 ·102 -3. 62 4 4 1I . ~1 ~ l·7 4
;6 ;6 - fr 'V 4 . 1 - . 13 . 060 30. 08 4 - 3.7 64
2Z ·916 6.21 9 - 3 . ~ 1 - 4 . 99~ 3 · 935 , 5. 5
,6 ,6
t : 9l ~ 6.2 47 0 .0 45 - 3. 9 - 4 . ~6 955 44 .
02 - 3· 52 3 d 37 45 -4. 37 6 . 1 ~ 1 45 . l 45 . 97~ - 4 . 613 50 .00 - 3. 283 50 4 .613 50 49 · 99 5·9 3 012 54 .988 4 . 311 - 4. 311 - 2· 985 g5 . 5 . 6 ~7 0. 02 8 l6 t6 3. 943 - 3 · 94 3 - 2 . 6~ ~ . 2 5 n: §72 - 2. 2 2 65 65 65 ·0 41 3.5 l;l -3' 6a d~2 - 1. 8 61 70 70 . 052 70 3·0 - 3 · 6~ . 9~ 3.6~ - 1. 464 2 . 545 ~5 .0 6 1 7 .93 i - 2 '~ 6 ~ 6 ~ 6 2. 0 40 - 2. - 1.10 ~ O . Ot ~ -. 81 -1. 535 ~ : m ~U~8 85 1. 5 35 85 85 ·0 - 1. 030 90 1.030 90 § O. O~ O
l:m -· W
5.0 6 - . 9 - · 525 ~U1e .525 95 10 0. 000 . 021 1 00 . 000 - .0 21 10 0 .021 1 00 - . 02 1 L .. E .. ra dl ue : L. E. r ad ius : 0·742 g :6 ~ T .E . radlus : T. E. r ad ius: 0 . 02 3 Sl ope of r adl ua thr ough L .E .. : 0. 095 NA CA 64A010 NACA 64J,Z10 §,t a t lo ns and o rdinat es g iven in p ercent ot airr o ll cb or c(1 I Up p er Surf a ce to _ ar S urfa ce Uppe r S urfa ce Lower S urfac e Ordinate St a tl on Or din ate St a tion Or di n ate S tat i on O rdi na t e S t a t i on I 0 0 0 0 0 0 0 0 .8111 -. 804 .~76 · 5 · 5 . ~ ::: ~llt : ~ 1.
·75 ·969 - · 969 · 75 • ~5 1. }7 - 1. 100 1. 25 1 . 22~ 1. 25 - 1. 22 ~ 1.~42 1. ~3 2 . 61 2· 5 1. 68 2.5 -1. 68 -1. 4p
2 . l 1. g5
g 5 .0 2 · 27 5.12 - 1. 9 3 5. 0 2 .6 g - 2 '627 3. 28 - 2. 316
a 7. 5 2. 05 - 2. 05 7 · 631
7 · 5
~: a~~ - 2 .600
10 10.132 3.1 99 10 - 3· 1 99 ~ . 792 15 15 -G .8 13 - ~ . O~O l · 813 ~6 : t~g J6~ - . ~ 0 20 . 272 20
- ' .272 ~ : ~~
25 .1 00 25 4. 606 25 - 4. 606 · 900 5.6 §6 - }'g ~ 30 . 083 30 30 - 3· 4 .8gz 24 · 9 1 ~ ~ : M 06 5 :: U~ 4 .9 3 ·9} 5 4 . +7~ 0. 045 - 3·71 46 46 955 44 . 6 . 2~ U 9~ 6 .2 - 3 . ~0 45 45
= u a
~6 : g~~ 6 .01 50 49 : ~l - 3 · ~ daM - 4 . ~ 4.3 8 - ~ . o 2 -4 .
~4 : m ~6 : gM - · 71 9
~~ t6 4 ·021 -4 .021
~ : m 65 3. 59 7 65 -2 . 3 !:Z - 3 · 597 66 ' 0~ ~~ : §~ : ~ f ~ 7 .0 - 1. 9 3.12~ - 3 .12 ~ 2. 62 }· 702 -2 . 62 - 1. 5~ ~5 . 06g
7t9~
-1.1 7 0 . 07 3. 037
I~ 1 ~ 2 .1 03 - 2 .103
1. 582 -1. 582 2 . ~01 85 85 i~J ~6 : g~~ : :~ 1i 1.0 62 - 1.0 62 1. ~ 1 90 90 - .2 95 9t974 Q5 · 02 7 - . 541 ·7 5 95 . 5 41 95 .021 100.000 - .021 100 . 021 1 00 - .021 1 00 . 000 - NATI O NAL ADV IS OR Y LaE. r a dius: 0. 68 7 L. E. radlus: 0.687 C OMM ITTE E fOQ A£A O .. AUTIC S T.E . radius: 0 . 023 _..!:!" _ rad! us: 0.023 Sl op e of r a dius t hr ough L. E. : 0 . 095
l
• •••••• • • NACA RM No. L6JOI •• • • •• TABLE 1. - Con el ud e d • • •• • • •• • • •• • •• • • . ....
• •• • •• •• • •••••• • • tlACA 64A410 NACl\ 641 A212 [Stations and ordinates given In ~tatlon8 and ordinates given 1n percent of airtoll chorcO percent ot: ai r foil cho~ Upper Surfa c e Lo w er Surfac e Upper Surface Lo w er Surface St a tion Ordinate Station Ordinate Station Ordinate Station Or dinate 0 0 0 0 0 0 0 0 ·902 . 3~0 .650 - . 678 1.013 .5 2 · 591 -· 901 1.11 2 · 918 - · 796 :~e§ - 1.0 1. 059 1.45 1 1.44 1 -· 969 g
ua6 d~; 1.135
- 1.33 2 . 09, 2 .724 - 1. 251 2.2l6 2.365 2 . 225 2 .635 - 1. ~03 4 .7 9 3· 03 5· 251 - 1.592 4 .849 5.151 7 . 230 3 . 14~ - 2 . ~2l , .865 7 · n0 -1. 9 12
. 380 10 .2 3 7 · B43 ~ . 84 7. §A -2. l
- 1.9~ . 432 10.1 - 3 .2 0 J:tGA ~.366 15.252 - 2 .2
4 · 42
1 .8~9 35B 15 · 151 6 70 .126 20 . 230 - 2 . ~0 - l·79
In t·
1 .1J 2 . 060 2 . 00 20.138 - . 200 6 .705 25·200 - 2 .499 2 .880 25 . 120 82 4 6.58~ 834 7 · 131 30.166 -4·i - 2.53~
2t · 2 . 00
6 .9 30 . 100 - 4 . 60 3 .871 9 7 . 414 12 - 2.,1 ,5. 9 4 6 3 ·922 7·1 9 078 91O - 4·741 7 · 552 - 2 . 36 0·090 l.i:.
.9 0 0 . 0~4 - 4. ~).4 7·522 45·050 - 2.266 t2 l4:§¥g
r· .1 7
g 5.0 0 - 4. 49 49 ·9 9 7·344 50.011 - 2.0~
r
025 0 3 -4 .27 ?O.O~ 2 . Z· 04 54.§Z5 4Pi g - 1.lJ. l d16 4. 98
5 .0 4
0.~7 -1. 8
.6~ -3 ·t
tt ·9 3 60 . 03
6.1l;E 966 - 3· 9 6.1 -1.086 65 · ~ .~15
70.1 n· 65.0~0 5 ·950 4 - 3· 03
6 . 92 4.
, . 4~0 -· l6O 70.0 4 . 903 6 ·936 - 2 · 537 p .126 .7 0 -. 60 7 .8l4
4 ~5 .075 4 . 197 7 .925 -2 . 037
8 - .229 0.1~ 3.96~ 91O A4 · 9 O.~O - 1.563 85.1 3 . ~33 3· 01 .852 - .132 A4 · 8 . 8 2 . 01 . 912 90 .104 2. 03/3 8 .8 6 -1. 1~9 -. ol6 6 9 .062
8 . - .7 1
1.028 928 95.053 - . 08 4 4 9 ·97 l : m
100.000 4 95·032 9 ·968 - .398
.021 100.000 - . 021 100 . 000 . 025 100 .000 -. 025 L . E. radius , 0.687 L. E. radius : 0·994 T. E. radius : 0.023 T .. E. radius! 0.028 Slope or· radius throug)'l L . E. : 0 .190 Slope or radius throug)1 L.E. : 0 .095 NACA 642A215 ~tatlon8 and ordinates given 1n pereen t or airtoil eborcjj Upper Surt.ace Lower Surt'ace Station Ordinate Station Ordinate 0 0 0 .388 1 . 243 .612 -1.131 .624 1.509 .876 -l· ig§ 1.107 O 1.323 - 1.
2.333 2. 13 1.r 2.6"67 -2.291 4.811 - 3·111 5. 2 t~§ 7 .§04 7·69
- l· 711
J.02 10.1~ - . 1 .811
nn 15·1 9
4a -4 ., 7.351 20.173 ~ . 827 - 5· 91 .849 25 ·151 - ~. 73 2 .8 ~:~5 - .121 75 30.12~ 8 . Z 4 3 ·903 09 - 6 . 238 L • 0.067 - 6.208 8·Z66 ~.9p ·9 3 8. ~ 45·i : 5:m 8.
~.
~§:m 9 .9 2 7 · 43 - ~.191 60.0~ U~ 65.0 3 : t:g$~ llU5~ 70 . 079 21 - 3. 416 ~.782 6,.9 ·926 - 2 .766 ~5 . 093 7 .~07 0. 111 4·017 - 2.147 ~4· 89 lO .891 85. l 3.0~9 59 - 1. Z 90 . 07 2 .0 6 8 . 24 - 1.06 95·039 1.039 4 9 · 961 - .549 100 .000 . 032 100 .000 -. 032 L.E .. radius: 1.561 T .. E .. radius: 0.037 NATIONAL ADVISOR Y S lope of radius throug)1 L . E . : 0 .095 COMMITTEE fOR AtRONA U TICS •• • ••
••
• • •• • . '.
•• • • • • • • • • • • • • ••• • • • • • •••• ••• •••• ••• •• 1.4 - - - 1'- ,
- -
- - -:::..::: -:=-:=-==-
- ~
--
-
~ ~
V
~ 1.2
-- NA CA 641A012 "~
I
~ N ACA 641-012
! -- - -
'-~ "
~
I
t--....
1.0
'- '"
I'- '-,- C\I '- ---..
~ r----..
>1 ::- '-
---
..
"'"
" .., " ~!
" s:: .8 '- cD oM oM c....
......
cD .6 cD H ::I til til Q) H Po.
.4 z » (") » ::a .2 3: z o NATIONAL ADVISORY r- CO-'MITTEE FOI AERONAUTICS I (J) o c....
o .1 1.0 .2 .3 .4 .5 .6 .7 .8 .9 o I-' C hordv Q se posit i on, x/c Fi g ure 1.- Co mpa ris on of th e o retical p re s su r e d istri b ution at zero lift of the NA CA 641 -01 2 and t h e NA CA 641A012 air f oil sections.
•• • • •• • •• • • NACA RM No . L6JOI •• • • •• .. ..
1.6 • • •• • • •• ~. ..
• • •••• • •• • ••
~ cL = . 01 Upp er su r f a ce
•• • 1. 2 !L •••••• • •
t--
t---
r
r----
~ ~01 Lo w er
surface
---
r--------
.4
.---
--
o o . 2 .6
.4 . 8 1.0
x/ c x v/ v c) ( p erc! nt c) (v/ V) 2 J..Qercent o o o o 4 . 560 . 495 · 90 0 . 949 2. 07 9 · 5 1. 06 3 1.031 ·75 1. 7 94
. 5Fs
1. 5 1.0 8b 1 . 04 2 1.3 70 ·7 2. 5 1.0 5 1 . 112 1 . 05 5 . 9 76 1 . 13 4 1 .065 5· 0 1. 44 7 . 69 3 7 .5 1. 74 7 1 . 142 1 . 06 9 . 563 1 . 989 1 . 150 1 . 07 2 . 485 15 2. 362 1.1 59 1 . 0 77 .,83 20 2 . b31 1 . 16 5 1 . 07 9 . 321 2 .8 20 25 1. 1 68 1.0 81 . 2 7~ 30 1.170 1.082 2. 942 . 244 2 . 99 6 1. 16 9 1.0 8 1 .2 17
~6 2. 985 1 . 162
1 . 07 8 .195 2 . 914 1 .151 1. 073 45 . 17 5 50 2. 788 1.138 1 . 067 8 . 15 2. 613 1 .120 1 . 05 8 .140
~ 6
6 1 . 100 2 . 39 1.0 49 . 12 6 65 2. 143 . 11 2 1. 079 1 . 039 70 1.859 1. 028 1.0 57 . 0 98 1. 55 1.03 5 1.017 . 085
~ 6
1. 2 48 1 . 01 0 1 .005 .072 .986 . 06 0 · 939 · 99 3 90 . 630 .964 .9 82 .0 47 . 322 95 .9 69 . 0 33 · 939 o o . 013 o L. E. radius : 0 . 265 perc e nt c T .E. radius : 0 . 014 per ce nt c Fi g ure 2.- N A CA 63 A Oo6 bas1c th1ckness form.
NATIONAL ADVISORY COMMITTEE fOR AERONAUTICS •••• •• • • • • • NACA RM No . L6JOl •• • .. ..
• •• • • •• • • •• .. . ..
• •
1.6 •••• • •• • •• •• •
~c~ = .05 Upper surface
•••••• • • / 0
/ I I I
/" 1.2
V- I I ~
~
!;<
r- .05 Lower surface ~ ~ '-.,
(v ) ot .8
I
.4
--
-----
o o .2 .6
.4 .8 1.0
x/ c x (v/V)2 v/ v ~vs.lv (percent c) ( perc~nt c) 0 0 0 0 3.465 .5 .658 .850 .922 1.961 .75 .791 1.017 1.0~4 l'b~ 1.25 1.003 1.00 1.3 1.03~ 1.391 1.13.2 1.0b 2·5
:~8~ 5.0 1.930 1.lb 8 1.081
2.332 1.089 7·5 1.18~ .,62 10 2.656 1.19 1.095 • 84 15 1.212 1.101 .;83 ;.155 1.221 .322 3.515 1.10~ 25 1.227 1.10 ;.766 .2l ;0 26 1.2;0 .2 b ;.9 1.10~ 1. 228 1.10 .218 ;.99~
G6 1.104
;.~7 1.21& .19~ ;. 78 1.20 45 .17 1.0~~ 50 1.18; 1.0 .15 ;.70~ ;. 46 1.159 .1;8 1.0~l
t6
;.176 1.1;2 1.0 .12; 65 2. 8 ;7 1.10 4 1.051 .109 70 2. ~ 57 1.0;6
LOp
.O~b 1. 0 2 1.021 .0 :3 2.0 , 5
~6
1.67 1. 0 10 1.005 .070 85 1.2 40 .980 . 99 0 .0 , 8 90 .8;3 1 .0 5 .9 ·975
1 .0;0
95 . 425 .9 9 ·9 ')9
. 018 0 0 0 L.E. radius: 0.4 7; percent c T.E. radius : 0 . 020 p erce n t c Fi g ure ;.- N ACA 6;A008 basic t h ickness form.
NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS .
....
.
....
NACA RM N o. L6JO l •• • · . ..
• •• • •• • • •• " . ..
1.6 • • •••• I-- C1. = .09 Upper surface • •• • ••
L
•• --.....
• •••••• r- 0- :::>-- • •
~
/' :::::::::-...
1.2 --.::::::::
~
'/
~ (.09 Lower surface ~
f/
~
.4
,.--
'---
o o .2 .6 .8 1.0
.4
x c / x y {vjV)2 v/ v b.valv (percent c) ( percent c) 0 0 0 0 2.805 .816 .880 .5 .7~4 1.83~ .75 .983 ·9 5 ·992 1.59 25 1.021 1. 1.2 50 1.043 1.;07 2.5 1.140 1.068
1.lJ7 .9~7
2. 2 1.200 5.0 1.095 .6 4 2. 91 22 o 7.5 1. 5 1.10~ 10 loll 3.32 • 3
4 ·u 1.2M
15 1.2 1.126 .38~ l·~50 20 • 00 1.282 1.132 .32 1.290 .280 25 4.714 1.136 ;0 4.913 1.294 1.1;8 .24~ .21 1.291 1.136
t :9~
~6 1.131
1.27~ .19~ 4J 1.25 1.122 .17 37 45 1.230 50 4.613 .155 1. 109 4.311 1.196 55 1.09 .137 60 1.162 .122 3.943 1.0~ 1.12 1.01 .108 65 3.511
t 1.08
70 3.044 1.042
.OA
2.545 1.048 1.024 .0 1
J6 .068
2.0 40 1.009 1.00~ 1.535 ·972 .98 .057 90 1.0,0 .044 .938 .969 .525 .030 95 ·900 ·949 .0 21 0 0 0 radius: L.E. 0.7 42 p ercent c T .E. ra dl us: 0.023 p erce n t c Figure 4.- NA CA 63AOIO basic thickness form.
NATIONAL ADVISORY COMMITTEE fOR AERONAUT/CS • •• •• • •• • •••• NACA RM No . L6JOl •• • • •• • •• c· • •• • • •• • ••
I I
I I
• • 1 . 6
_c~ = . 12 Upp e r surfa ce
•••• • •• • •• / •• ( • g..........- •••••• .. .
t?:: I-- / ~
~
1.2
--
~ ~
1 /
~ .12 ~ Lo we r surfac e
. ~
2 I
~
.8
(~)
.4
r- -I--
V-
r- f---- ~ f-- o o .6 . 2
.4 .8 1.0
x c / x y (v /V)2 v /v 4v alV (D erce nt c ) ..1..ne r c en t. ....c..l 0 0 0 0 2 . 361 . 686 . 828 1.701 . 5 · 973 1.173 . 924 . 961 ·75 1 . 51~ 1.25 1.492 .985 . 992 1.25 1.066 2. 5 2 . 078 1.1 36 . 935 2 . 89 5.0 1.229 1.109 . 679 3. 50 1. 265 1 . 125 4 7 . 5
: G~~ 10 1.291 1.136
l· 994
1 . 151 15 1 . 324 . 384 . 7~7 1.344 . 325
5.2 l
1.15~ 25 5. 66 1.16 . 281 1.355 1.16 30 5. 901 1.360 . 248 . 212 5. 995 1.16~ 1.3~7
~6 1.30 . 196
5. 957
1.1G
5. 792 1.312 1. 1 5 .174
50 1. 129 15
5 . 51~ 1.274
. t
1.23 1.111 . 13
G ·
t6 .1 20
. 700 1 1 . 091 1.14 . 106 65 4 . 186 1.1~
1.°l0
3. 621 1.08 . 0 2 1.09 3. 026 1 . 051 25 . 0 9 1.0
J~
1 . 003 .066
2 . ~6 1. 00l
85 1. 26 . 96 . 982 .O~ 90 . 962 . 0 1 . 22~
:A§6
. 62 95 .938 . 0 9 100 . 025 0 0 0 L. E. r adius : 1 . 071 percent c T. E. radius : 0.028 perc e nt c Fi gur e 5 .- NACA 6 31 A0 12 b as i c thickn ess form.
NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS •• O'. • O'. .
•••• NACA RM No. L6JOI O'. .
• •• .. ..
• • •• •
= .18 upper surface
• •• v-c~ • •• ./ · . .
1.6 ••• ---.....
• • 0 ----..,
• •• (
O'.
f-"
~ /
-
v • • •••••• --::
.. . ~
/ ~ /
~ 1.2 '" .18 Lo w er surt'ace
~
I;
~
2 I(
~
~
(V ) .8
I
.4
~
r---
v--- -
r--
I-- !--" ~ I--
I'--
r--
o o .2 .6 .8 1.0
.4
x/ c x (v/ V)2 v/ v l:J.vaiv ( percent c (p erclnt c) 0 0 0 0 1. 930 o .5 .7 42 1. 504
1.~
1.
.§O8
·r
: §~
I:Ng 1.
1J~
• 39 2 . 5 1. 120 1. ° 58 2.57~ · 2 °5 2 1.121 .669 5·0 1. 57 ~.61 .382 7.5 1.323 1.1~0
:4~~ 10 1. 61
1.17 4 .9~ 15 1.08 1.187
4 5.9 38
• t
20 61 1.1 1. 4 37 .32
6. i
t 25 1.20 .282
7.0 ~ 1. 45 ~ 30 1. 4 6 1. 2 10 .250 7. ~ 7. 9 1. 45 .220
4 1.2.0J
7. 4 35 1 . 435 .196 1.1~ 1 . 3 6 1.12 45 .17 4 t~l~ 50 1.161 1.39 .152 1.296 1.138
6.~~7
.13~
t6
5. 20 1. 237 1.112 .11 1.175 .10 4 1.08~
t t ~ 70 1.115 1.05 .090
3.73 1 1.05 5 1.027
J 6 :g1l
2.9 91 1.0 00 1.000 85 2. 2 52 .0 2 ·950 .975 90 1.5 12 .0 0 .9 49
4 .~OO
.77 2 95 • 50 .922 .028 . 032 0 0 0 I L.E. r adiu s: 1.630 p eroe nt c T .E. radiu s: 0.037 p erce nt c Figure 6.- N ACA 632A015 basic thickness t'orm.
NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS •• • • • ••• • NACA RM No . L6J Ol •• • ..
• • • •• • • 1.6 •• • • • • • •• • • •••• • • • • • • ••
~cl = . 02 Upper surface
• 1.2 --jJ •••••• • • ~ r---.
~
--=-
~.02 Lower surface ~
--
.4
---
-
o o .2 .8
.4 .6 1.0
x/c x y (v/V)2 v/V AvaiV (p e rcent c) (percent c) 0 0 0 0 4.688 .485 1 . 019 1.009 2.101 · 5 1 . 046 . 585 1.023 · 75 1'7J8 25 1. 2 1. .739 1 . 076 1.037 1.016 1 . 106 2 2· 5 1.05 . 980 5.0 1 . 118 1.057 .69.4 1.3~4 1.6 1. 126 1.0bl 7 · 5 10 2 • 82
'4 1.919
1.06~ 1. lR 2.283 1.11 1.06 15 . 382 1.072 . 321 2·557 1 . 14~ 25 . 278 1.15 1 . 07~ 2 . ~51 30 2. 96 1.15 1.07 . 246 1.162 1.078 . 219 2·977 R6 2.
1.165 1.079 .197 9 9 45 1 . 075 .177 2 . ~ 5 1.1~ 50 2. 25 1.1 1.069 .1 2.6 1 .125 1 . 061 .1 3
4 5
g
~6
1 . 107 1.0 2 .12b 2.4~ 65 2 .1 8 . 112 1.03 1.08~ 70 1 . 9.07 1.06 1.032 .0~9 1 . 602 1 . 04 1.021
.0 l
~6
A 1 . 285 1.01 1 . 009
. 07 85 . 061 7 . 9 .9$6
'l6
t
90 • 49 . 9 4 .9 2 .047 95 .331 . 967 . 033 · 935 . 013 0 0 L. E. radius : 0.2 46 percent c T.E. radius: 0. 014 percent c Figur e 7 .- NAC A 64A006 basic thickness f orm.
NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS ••• •• • •• • • •• NACA RM No. L6JOl •• • • •• • •• 1.6 • 0 • • •• • • •• • ••
o . •
••••
~ cL = .046 Upper surface
• •• 0\ L: • •• I •• 1.2 •
r::=----
~ .....
I ~
• • ~
V ~ ~
Lower surface
~.046
~ ~ .8
.4
l------ !'-- o o .2
.4 .6 .8 1.0
x/c x y (v/V)2 v/V AVa/V _(J)ercent c) (oercen t c) 0 0 0 0 3.546 .6 46 1.972 ·5 ·947 ·973 8 1.002 .75 .7 1.697 1.0~
A 1.0 1.033
1. 1.352 ·9 3 1.122 .971 2·5 1.059 1.~53 5.0 1. 63 1.073 .69.2 1.1~1 2.245 1.0 7.5 b4
LIt
·4 10 1.0 • 81
A4 1.17
2. a
15 1.191 1. 91 .382 3·0 20 1 1.201 1.096 .323
l
3·t 1.20 1.100 25 3. 81 3.866 1.21
:~l1 30 1.103
f
1.221 .221 3.972 1.105
t3 1.225 1.107
3.998 .1~8 1.211 1.100 45 3·921 1.191 1.0~1
:id 3.7ll
1.lb7 1.00 .1 3·5 g~ 1.068 3.234 1.141 .125 1.n 1.0 .111 65 2.897 70 2·521 1.08 1.01
G
.~8 2.11 1.026 1.053 • 4
~3
A 1.69 1.020 1.010 .072
85 1.278 .0 · 987 9 ·9 93 90 .858 .0 5
4 ·951 .975
. 914 .032 95 ·438 .956 100 0 .018 0 0 L.E. radius: 0.439 perc e nt c T.E. radius: 0.020 percent c Figure 8.- NACA 64A008 basic thickness form.
NATIONAL ADVISORY COMMITTEE fOIl AERONAUTICS •••• • •• • •• •• NACA RM No . L6JOl •• • • •• • •• I' • •• • • •• • •• • • 1.6 •••• . - ..
• •• •• . 0S Up p er s u rface
c1. =
• •••••• ~ .. .
::;; ' 0_ 1-- - ~ I--- 1.2 -.....;;:;;;;: ~ ~ ~
!/ K:-
surface Lower .08 ~ I (~ ) .S
"
.4
V- I'--- o 1.0 .6 .8 o .2
.4
x c / x '1 v/ v Ilva/V (v / V)2 (percent c) (percent c ) 0 0 0 0 2.868 .S04 .S68 .5 .932 1. S 45 .969 .976 1.603 .75 .9~ 1.25 1.0 1.021 1.300 1.2 2 ~ 2.5 1.6 8 1.130 1.063
:~~ 5.0 1.178 1.085
2 .327 1.201 62 2.905 1.09b 7·5 ....l.
-
- 10 • 80
'4 3.199 1.103
1.21~ 15 1.23 1.113 .382 ~.813 20 1.120 .272 25 .324
1. t
25 4.606 1.2b 1.125 . 28 0 30 8 1.129 .248 1.2J5
4. M
1.2 2 1.132 . 2 21 4 . 9
~~ 1.2 88
1.135 .199 t :A , 1.268 1.1 2b 1.2 40 50 1.114
4 .~ ~
:~~
1.208 .1 0 4 .38
n
i:~ ~ 4 .0 21 .124
1.174 65 3.5 97 1.139 1.067 .109 1.102 b 70 3.127 1.050
'OA
2.623 1.063 1.031 .0 3 1.02 1.011 2.103 .070
1 1.5 82
~~ .98 .990
.O ~ 90 1.062 .0 3S .969
'A .031
95 .541 • 93 .945 .0 21 0 rad1ua , L.E. 0.687 percent c T.E. rad1us s 0.023 percent c Fi g ure 9.- NA CA 64A010 basic thickness form.
NATIONAL ADVISORY COMMITTEE FOIl AERONAUTICS ••••
• •
• • •••• NACA RM No . L6JOl ..
•••••• • • •• • • •• • •• .. .
•• • • ••
I I
• •• I I
I
• • 1.6
~cL = .13 Upper surrace
••••
• ••
• ••
/
•• • ( 0- •••••• ~ . . .
:::::::
t>--
r-
~ /" t--- ::::-"
1.2
----
V ---~
( /
~ ~ ~.13 Lower surface
~ 2.
~
~
.8
@)
r--
- r---
V-
=
r--- i-- f----
-
o o .2
.4 .6 .8 1.0
x c / x (v/V)2 v/v AvaiV (percent c) (Derdnt c) 0 0 0 0 2.408 .961 1.720 .5 .~92 .8~0 1.158 1 .75 . 93 .9 5 1.5 1.25 1.006 1.003
4 1.46~
1.2~ 2.5 2.01 1.127 1.062 .9 1 5.0 2.788 1.201 1.096 .6 1 1.111 60 1.235 7·5 3.~64 10 1.2 1.121
'4
. J8 AA 1.2
t5~6 15
.3 3 1.14.4 20 1.308 1.1 5.132 .325 .281 25 5. 34 1.151 1.32~
g
30 5. 09 1.3 1.156 .249 .221 5.965 1.3 6 1.160
~6 1.164 .199
1.35~ 5.~~3 1.32 1.152 45 5. 3 .177 50 6 1.289 .157 1.13~
5. 4a
1.250 1.11 .139 4.
t6 .801
1.099 .12~ 1.20~ 65 4.289 1.16 .10 1. 79 70 3.721 1.11 1.057 .0~4 3.118 1.071 .0 0 1.035
J6
2. 00 1.011 .068
1.02e
g
85 1. 82 .0 6 .97 .987 90 .0 2 .962
1.2tt .~25
. 6 . 73 .029 95 .934 100 0 0 .0 25 0 L.E. radius: 0.994 percen t c T.E. radius: 0.028 percent c Figure 10.- NACA 641A012 basic thickness fonn.
NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS • •••••• • • • •••••• NACA RM No. L6JOI • • •• • • •• • •• o. .
, .
I I •• • • •• .21 Upper 8urface • •• Ct = • • 6.
1.6 • •••• / • •• • •• •• 0 "",-
r- 0~
•
-
•••••• • • ~ ~
r-------
V--
~
/ ~ L
1.2 ~
~ "-.21 Lower surface
I I
~ ~
~
I ~
.8
/
.4
I-- r--
-
~ r--
t::= r- ~
I'--- ~
t--- ~
-
o o 1.0 .2 .8
.4 x/ c .6
x y (v/ V)2 v/ V V tna/ ('percent c jQercent c~ 0 0 0 0 1.956 .5 1.193 52 .6~8 .8~ 1'4 .75 1.436 .7 9 .8 1. 04 1.25 .936 1.189 .96 1.81~ 0 1.110 2·5 1.05 .912 2'4 5.0 1.226 1.107 .671 ~. 77 .202 1.280 7.5 . ~ 52 1.lr 1.314 1.16 4 .799 • J8 15 1.360 1.1 6 ~.732 .3 ~ .;2 .423 1.1J9
l'GiO
25 6.926 .28; 1. 3 1.19.
;0 1.196 .249 7.2~0 1.l£O 7.4 ; 1.202 .222 1. ~
~6 1.207 .201
7.487 1. 45 1. 414 1.18~ .17~ l·;l~ 50 1.;64 1.16 .97 .15 1.311 1.1 45 .1;1 6.51~
~6 1.2 1.120
.121 5·95 5
g
65 ll 1.19 .106 1.09.5
4'g
• 00 70 1.1;9 1.061 .0~1 ;.847 1.079 .0 8 1.0;9
~6
3.084 1.020 1.010 .065 85 2.321 .961 .0 ; .980 90 1.558 .0 1 4 .~01 .9 4 ~ .795 1 .027 95 • 43 .9 0 0 .0;2 0 radiuss L.E. 1.561 percent c radiuBS T.E. 0.0;7 percent c Figure 11.- NACA 64 A015 basic thickness fonn.
NATIONAL ADVISORV COMMITTEE FOR AERONAUTICS •• • • •• • •• • • • NACA RM No . L6JOl •••••• • • •• • e . • • • •• 1.6 • • •• • • •• .. ..
. . .
•••• • •• Up p er surf a ce
• •• = . 01
•• /.CL 1.2 / •
rzO
•••••• • •
r---
I
I
t---
['--...
r-"
r-- .01 Lower surf a ce
~
.8
.4
--
o o . 2 .8 1.0 .4 x/c .6 A Y (v/V)2 v/v t:.valv (percent c ) (percent c) 0 0 0 4 . 8r .464 1 . 017 2 .1 5 · 5 4 1.°l .75 1.021 1.73 .56~ 1.0~ 1. 1.05 1 . 029 ·71 1 . 365 .981 1.080 66 2 ·5 .9 1.0l 5. 0 1.101 1 . 313 1.09 .688 1 . 112 7 · 5 1.~91 1.05~ . ~62 1. 24 1.120 . 80
LOt
15 2.194 1.131 1.0 3 .382 1 . 06 . 32 1.1l9 2 · ~A4
g
6 25 2. 7
1.1 5 1.07 . 27 30 2.842 1 .149 1.072 . 246 1.153
2 . 94~ 1.07 t .21~
&6
2. 99 1.157 1.07 .19 2.992 45 1.159
1.07 l
. 1~8 2 .925 .1 1 1.1~7 1.0~ loll 1.08 2 · 793 .143
~6
2 . 602 12 1.060 .127
1. t
65 2.364 1.10 .112 1.0~2 70 2.087 1. 083 1.01 .0~9 1 · 775 1 . 059 1.029 .0 ~ ~6 1.
1.032 1. 016 4 7 .o~
e
85 1.03 1.003 1.001 .0 1 . 727 .986 ·973 .047 95 . 370 .9 36 . 967 . 033 . 013 0 0 L. E. radius: 0 . 22l percent c T. E. radius : 0 . 01 . percent c F igur e 12 .- NACA 65A006 ba sic th i ckn es s f orm .
NATIONAL ADVISORY COMMITTEE FOR AERONAUT ICS •••• •• • • • • • • •••••• NACA RM No. L6JOI • • •• • · ...
• •• • • 1.6 •• • • •• . ~ ..
• • •••• • •• • ••
~ c1 = . _?5 Upper surface
•• 0" · .
1.2 •••••• ~r- I I~ ':::::: • •
~
1---.05 Lower surflice
/? ~
~ ~
/
.8
"
·4
l...-- ""--- o .2
o .4 .6 .8 1.0
x /c x y (v/V)2 v/v ~valV (percent jQer~ent c) cJ 0 0 0 0 3.698 2.010 . 615 .986 ·5 ·973 1.001 1.000 .7 46 1.693 ·7 5 1. 25 1.019 · 951 1.33 1.0~8 2.5 1.303 1.08
G 1.0~3
1.1 27 1.02 : ta
5·0 1.749 2.120 61 7.5 1.145 1.070
·G 10
2.432 1.157 1.0~6 • J9 15 2 .926 1.04 .3 2 1.1~t 1.1 08 .3 22 3.301 1. 9 25 1.093 3.585 1.195
.2l
30 1.202 1.096 3 .7 91 .2 7 3.928 1.207 1.099 .21 ~
G6 1.213 1.101
.19
§:9~~
21 1.103 .l 8
1. 4
~6 b 1.21 1.102 .1 1
,.e9~
1 1.191 1. 0~1 .1 ~ 3·l
t6
3. 5 1.167 1.00 .12 67 .112 65 1.0 3.1~5 1.13~ 70 1.10 1.053 2.7 ~ .0~8 .0 6 1.076 1.037 2 .~ 4
~6
1. 98 1.041 1.020
.OZ3
1.002 85 1.430 1.001 .0 0 90 . 961 .980 .0 46 . &6 0 . 89 .916 .031 ·957 .018 0 L.E. radius: 0.408 percent c T .E. radius : 0 . 020 percent c Figure 13.- NACA 65A008 basic th1ckness form.
NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS • •••• • •••• • NACA RM No. L6J OI •••••• • • •• • • •• • •• 1.6 • •
•• • I I
I
I I
• •• • •• .10 Upp er s u r fac e c1 = • • / •••• • •• • •• ~I---- ~ t::-.
•• 1-0""" 1.2 • •••••• ~ . . .
r;
~
< 0 Lower ~ s ur fac e ~
((
~
·4
~ I--- r- o o .2 .8 1.0
.4 x/ c .6
x y (v /V )2 v/ v 6valV (Qercent ( percent c) c1 0 0 0 0 2. ~ 8~ · 5 .947 1. 7 . 7 6~
: ~4~ .92 .974 1. 9
·7 5 1 . 010 1. 25 1 .1 83 1. 3 03 1 . 0~ 2 .5 1. 6 23 1. 08 1. 0 .936 2.1 82
A 5·0 1.1 4
. 679 1.0~1 2 . 6 O 7.5 1. 176 1.0 4
: G5~
3 .0 0 1. 09
G
1. 1 9M
15 658 1. 21 1. 10
.3~2
G · 20
.127 1.111 .323 1.2~ 4 4. 4 83 1. 2 7 1.117 .281 30 1.121 4.7 42 .249 1. 227 4 .9 12 . 2 22 1. 2 5 1.12~
G 6
1. 272 1.1 2 .198
t : 9A ~
2 1.130 45 1. 77 .1~ 8 50 1 .2 71 1.12 4J6 3 .1 1 4. 63 2 1. 24 1 1.11 .144
~ 6
1. 2 08 .127 4 . ~ 0 4 1.~ 9 65 1.17 2 .111 3. 99
1. E
70 3. 4 32 1.0 6 1.133
:g A4 1.0 1
2 ·9 12 1.0 45
~6
2 .352 1.023 1. 07 .071 85 . 9 9 8 1. 7J 1 . 99
.oa
90 1.1 8
4 4 .0 5
.94
'A 9
.6~ 95 • 93 .9 5 .02 9 0 0 . 0 21 0 L .E. rad 1 us: 0 .639 p erce nt c T.E. ra d 1u s: 0 .0 23 p erce n t c Figure 14.- NACA 65A010 basic thickness form.
NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS • •• •• • •• • ••• • • NA CA RM No . L6JO l •••••• • • •• • • •• • •• · . .
1. 6 I I I I •• • • ••
~ L = . 15 Uppe r surfa c e
• •• • • / •••• ., ..
• •• I-- 0--.
-. ~
~
V-
r-----=:: ~ ••••• : 1.2
-
~ . . .
K
1--.1 5 Low er su rfac e
( /
~
~ ~
'(
~
I
.4
r--
~ c--
-
-
-
f....--
'---t-
-
o o . 2 . 6 .8 1.0
.4
x/ c x y ( v/V )2 v/v ~v alv (Qerce nt c ) (p ercent c ) 0 0 0 0 2 . 520 . 9 13 .824 ·5 ·908 1. 7~7 1.106 .8 83 .7 5 1. 5 3 . 9~ 0 1. 1. 414 . 969 ·9 4 1. 4 2 ·5 1. 24 2 1. 08 1 ·21 1.0~ 0 1. 166 1.0 0 5·0 2 . bl~ . b72 7·5 1.20 ~ 1. 09J . ~5 7 1. 22 1.1 0 . J7
P l7
1 .2 63 15 1.1 24 .~ 2 .3 ~2 .9 6 1. 285 1. 1 . 24 25 1.1 1 . 28 1 5.3 3 1.3 01 30 1 . 31 5. 69 3 1.1 46 . 250 1. 32 1.1 51 4 5. 89 7 . 22~ 46 1 . 332 5· 995 1.1 54 .19 1 .338 .178 45 1.1 57 5· 7J A 50 5. 2 .1 61 1. 329 1.153 5. 544 1. 29 1.13 .143
g 6
251 .126 A 1. loll ~ .1 44 65 . 65 .1 11 1.0 97 1. 2 0 ~ 70 4 . 02 1 1.15 1.075 6
. Oa
1. 104 .0 2 3. 4b 1.051
~ 6 A
1. 05 1 1. 0 25 . 069 2 ·79 2 .1 06 · 92 7 .99t
: g4 ~ 90 1.4 13
. 9'6 7 . ~ 3 .7 19 95 . 71 . 0 27 · 933 1 00 .0 25 0 0 L.E. r adius : 0 . 922 pe r ce n t c T .E. r ad i us : 0.0 29 p ercent c Figure 15.- N ACA 651A012 basic thickness form.
NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS •• •• • •• • •••• • •• •••• NACA RM No . L6JOI • • •• • • •• • •• . . .
1.6 •• • Upper surface
• •• c~ = .22
• •• • • ~ . ....
• •• I-""
y
• •• •• V--
~~
-----
/ ~
••••• : 1 . 2 "-......
• •
/-
r- . 22 Lower surface
~
~ ~
'/
~
1/
I
.4
r--
~
r---
V--
I-- t-- r--- f.--
'--- I----
r--
-
o . 2
o .4 .6 .8 1.0
x/c x y (v/V)2 v/v ~valv (percent c) (percent c) 0 0 0 0 2 . 048 1 .131 .714 86 · 5 l ' a
: ~~a 1.371 1. 17
.75 ' 'J81 1.25 . 91 . 944 1.1~5 l ' 7JO 2 . 2 29 1.0 1.0 .8 0 2 · 5 9 g . 660 5·0 1.17 1. 089 3· 255 1.115 7 · 5
G .962 1.2~3 53
1.20 1.131
'a . ~6
5:agg 15 1.328 1 . 152 . 3 2 6.198 1.166 . 326 1.3~9 . 282 25 6. 734 3 1 . 1~6
loG
30 7 ·122 1. 01 1.14 . 25 2 6 1.416 1 .190 . 227
7 ' l7
l6 27 . 204
7 . 96 1.4 1.195 . 181 45 7 . 467 1.437 1 . 199 50 1 . 191 . 161 ~ .269 1 . 41~ 1.36 . 142 · 903 1.1l0
~6
1.311 .124 6.393 1.1~ 65 loll . 10 1.2~9 5 . 7~2 70 1.16 1. 089 & . 0 3 . ~ . 282 1. 123 1.060 . 0
J3 1.0 b 1 . 02 8
3.451 .067
g
.9 6 · 993 2 . 5~8 . O~ 90 . 0 .956 . ~13 1.J 3 95 . 7 . 41 .026 · 917 100 0 0 0 . 032 L. E . radius; 1.44 6 percent c T. E. r adius ; 0. 038 percent c Fig ure 16 .- NA CA 65 2 A0 15 b asic t hickness f orm.
NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS •• • • • ••• • • •••••• • • NACA RM No. L6JOl •• • • •• • •• .. .
•• • 2.0 • •• • •• • • •••• • •• • •• •• • •••••• .. .
1. 0
~
\
o Y c
-
c
IIkllllliEl
o . 2 .4 .6 .8 1.0
x/ c = 1.0 = 1. 40 cL i ai Cmc /4 = 0. 2 19 x Yc dx dYc/ A viv = pR/4 PH percent c p erce nt c ) 0 0
------- -----
-----
. 281 · 5 0. 47534 · 75 . 396 . 4400 1. . 60 3 . 39 31 2· 5 1. 055 1.0 92
4 . 33 04 0.273
5. 0 1.803 .2 '714~ 7. 5 . 2337 2 . 4~2 2 .9 1 . 20618 h 15 0
l ·9 3 . 16~46
. 651 . 13 52 .10 73 >1 .0 96 5 . 2~ 7 . 274 5. 7 2 . 08~9~ 6.120 . 06 9
l~
6. 394 . 04507 ) 1.100 . 275 45 6. 571 . 02559 6. 651 . 0060 6. 631 -. 0140 . 276
~1. l04
~3
6 . 508 -. 03537 6.274 1. 108 -. 0~887 . 277 -.0 610 3 1.1 08 . 27~ 5' r -. 12058 1 .112 . 27 ~ . 01
~~
• 73 -. 18034 1 . 112 .278 85 3. 607 . 210 . 8~0
-. 2l O
2· 452 -.2 521 . 5 8 . 147 1. 226 95 -. 24521 .3 68 . 092 -. 24521 0 NATION AL ADVISORY COMMITTEE fOIl AERONAUTICS Figure 17.- Data for NACA mean line a = 0.8 (modified).
. ' • • •• • ••
•• • • •• • • •• • • • • ..
•• • • • • • • • • • ••• • • • • • • • • • • •• • • •••• •••• ••• •• _n + __ ._ . n.
1 +- 1 + · ·· =j n:Hn-F- I+ I- + + +-b++-l-+ I I I I T l-+++ +- 1 +- 1 J L L l l l ·I· 1 1 I 1· 1 :'1' 1 I H- I-H 1 -+,-j-4;-J ++-J· I -H·-J=
I I I l i n I I . I . H- I- -H<I I ;, b ~
L-r . f'1=: I-
h-J-.- I --J
0.2 0c simulated s p lit na p de~lected 60 1 ++ ++ ++ .H+ +++ .H fF l.f l l f l+Ft++ i% f ffHm + ~ '\ I I I + +-H-l-+'
~ ~t~~~h{oUghness . ~ r l +': r ~ . .+ ~ j J R i I ' Ilfr l -r l -t lt llll il l
I '~ . f'" T . r - r r If' &. I' I- F - :.1 - k 06 ~ - I ., ' ; rf I j "W ....... ~ r ++ H :!" ~ .
f-~ -+ - J. t !. -t- I-r+. 1 -'- ... .. 1 - ~ . t-t- I -b . .. !'" I- ~ r . r- ... ~~I -t-- I - • . D. s t~~a . ': , ;:= .. • •. == ~ = 1 -1- 14 k T j - IT": 1-- J- +- r ·r ~ . 11. 1- + " 1 ···,··1- ~I -',- Ii. .! .. r-t- l±l ± ± ±± .1 1 + '
H -+ -+ I ~ ~ --." +-- - + '1 ~ -j_. ~ H ~ . 12LLl J I .I :T ~ +. , - '1'\ . ,-- -r- t-
I -LH L': J J " 1 II I L I . b h..., '. ' 1\1 1\ I .". r "'< Ii 11t if1j .
I I r" . '-':-~ -r- Jf . I b~ R t: . 1/ I If II t I I
I I!" If : !!! * ----1-. 1-' lb. i= t- .1 '11 I ~ ~ I -I 1 1 1
l -:t . 1 -' t .... 1"'" -j I "" 1 #. 1 4 . .. <> 9 ·0 x 10 ~ . i'Il 1 C' I7 'c ... iJ Plt
II h n ~ • • , J, .-I- .,... 0 6 0 1 ~ I
I I . ~ r -'-.~:' .i! ~ ,. . 0 3 :0 hi: F ~ ' to ~ ~ I- .. I/I ~
T I r: ... I T If ' 1Lj 1p4"'~ D. S tandard . . p,.. I.!!-tl' • I;;:; ~ v
CIII fj J J rou ghn es~ T 0. "" r.;_ ~ n R
LJ;;.!1d.r.;:..;: : 1 Ti ~ . I... -+ ~ .: c . ' 6.0xlOb .l . .. ..... "1li ,. . liI" i'I"" :T ' " . . ...b6 - l;;,. . , ' " " . 1 ~b. 1. . + 1 ~+ 1J1 ,. ..,( ~ l -/,-1 4'-1 .. 1 1.1 f-+, I I I .1 1 d- H- I + + -+- Hrl l" I .. I I d- H-! I I I I :: I . I I ~ f-frH--t-i
H+ l :H ~ I -M I- ftlltM-l c'r l -i H"
7 · 1 1 1 ·ln l -;-+ + +- l n-Jd- ~ ¥ . t1tH .. -p.,H I 4= I -4d-+ 1 1'.1 '''1: 1 4 1 + 1 -'
II I + + +
1 -+ + -++ ~ I t l i ~ l"'- ,tI l
H.+. l tu. l .t ttI8 -t t. tH: P+ I .... ' .... , .::.,.:. ' .: I . , z
a . c. p osition » ~ ': 1 1 1 1 1 4 f-ef.~~ (') R x/ c y/ c » + 1 -1' 11 1. <1' -I.e " n ''''f l- 0 9 . 0 x 106
.25 4 mt 1 +1 +1 + ++++ + +1 r~ I--- I 4'- I "
-,Ooa ;:0 Jl G 6 .0 .01 . 253 i,.,- 1! ' 1 '.1 I J I-++--H+H \ ~ ++ I H' 0 P< I 4H-l :rl=+ 1 + ~ + 14 I . I l .f I 1 I 1 I 1. 1' ..
o 3. 0 . 2 50 3: J ~ , -=- I I H I HI IJLL1o: z II I [ 1 '1 Fm1 ". ;00 ' ·'~~·; · #iI fM111 ' I~ :l ill l l l :I· I I ,J I I , l l l l l l l ll l l · I r I I I TI I IT IT I . n:.p .. :e . ;l :: : e d 6 ° . c=== ? == i r E :: i7t ::, : /·d ..... .. .. .. . j .• • " ;:: i « < (J'l :.,;; ." '. .... . I I I I " I I I I I I • ... ....•... .. .. .. . . ". " . .
c...., .0 1 1" 1 ·1 1 '1 1 ta il I I J ilo hl n f jg te hf t ~WFh[~ + I .. I 'k l df4- ll l .. tf.ffl n= i FrJf F ~m ; 1 1 f a1 f t> 1 ~~b n t ~ B all l i $~~~ f-' w..:..
r - -, :1 r --T-- T --T --- ' --- T-- -r Uj - -T -- T --- j I I I I I I I I , I 1 - +- - ltd · I .: j; J ,I 1 ': 1 :- :1 ;;;, 11 : 1 - i I ;;: /: I : 1. I : 1:: 3:: 1: L .•. • _ ... _ . , - • ' .
NATIONAL ADVISORY Fi gur e 18 . - Aer o dyn am ic characterie tics of the N ACA 63A010 airfoil section , 2 4-inch chord; 'roT t est 983. COMMI TT EE rot AfRONAUTIC S.
' ..
• • • •• •• , '.
• •• • • •• • • •
•
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l iJl !l! ,.. ,:l.JLl.TL.L.I.l . U .. .. .. Ii .... ;~·:H 0 9 ·0 x 10 .257 -.0 24 3: .. .. ... 0. 20c simulate d split t.. , .. I;li.'!' .I.;':!:·: 'j": "" 0 6.0 .257 - . 037 +++-HH"'+++ -l- +-~ z o e- m c...., ir;;;'~~~" '; ~;:"'i; :~ ~:~: ; ':' ~ , ' ~ ~ , , '. ,' ':, : ;,: ~' ! . ~ ;, ~ ~~ ' ~t~. ~, ~ ,, '. :~ ~ ~":l": ~ ~ ~ ~ i ; ~ ~£IT~ ~ ~;: :' ;, ~ . O o I-' Pigure 19 .- Aerodyn am ic ch a racte r i s tics of the NA CA 63A 2 10 airfoil section, 24 -inch chord; TDT test 970.
•• •• •• •• •• • •• • • • • • • • • • • • • • • • • • • ••• • • • • • • • • • • • • • • ••• •••• •••• ••• •• •• ::> . fl 1 1· 1 I I I I I I +H -i -+ + ·+:: ll ll Tf l+ ++ + +++ H+t + tI-H fl ·I I I· I ·I I "1 11111111111 1· 111 .11 I I T I I I I I L I 'l l
m l ~ ' ~I ' 1 T 1 -1 H- I Mp -r ,. kH " .. cb i I..!
..... ." O. 2OC simulated split I "t- ..1 .. . .... ..... flap de flee ted 60 0 , R !
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. 0 z F
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l 1MifM *f# lilihlJjJt* -t t t ~ E l· j±lltb rT ' :·· LJ 7m ~ ~_ I ··· ¥'j~~ I ; ~ llli!tf~Ftf · · · 1~1·1 · 1 ;;· 1 · 1~~ i·· · I ;· I ·· ' f-' Figure 20.- Aerodynamic characteristics of the NACA 64AolO airfoil section, 24 -in ch chord; TDT test 956 .
,; •• •• • •• •• .. . ..
• • • • •• • • • • • • • • • • • • • ••• • • • • • • • • •••• •••• •••• • •• ••• •• 2.8 k-4--l--I- I : I 1 1 1+ l lFf1+ FH f l+ ++HI -t I I I I I I· I t I I I T i l I' T I I' ' ''''ld ' d' ' 1' , .. , , ., . flap de fl ect ed 0
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II I 1. 1 1 I f2l l lft MIJnfa-1 ghlot- t ~' a[ [ b ~! 1·1·1 t r i l l <I I P_ ~ - l h f" ~ ;W; It- 1t hl h h I JJ;10f .. b ;[- ~ bdI J1 ,I I ]l t ~ : I 'r ~ ' O o .,L , __ ~ _ I . 1.
f-' Figure 21. - Aerodynam i c cha r acter i st i cs of th e NA CA 64A2 10 a ir fo il sec tion ; 24-in c h cho rd, TDT t es t 969 .
. ..
..
•• •• •• • • • •• • • • • • • • • • II • • • • • • • ••• • • • • • • • • • • •••• •••• •••• •••• ••• •• 2 . 8 • C I ;:> ",'1;;; ,: g' : t ~ , " I' I 1 :1 I I I I I t I 1 1. 1 ;I:·:!;: ........
'" 0. 20c simulated sp lit ....
, .J . " fla p deflected b Oo '", I ;: .......
. ~ :; :::: 2. R l il>R l- 6 x 10 '<iI 1 III ....
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.~ :~Ii;:; I .,. ,: 6 I , " 6 x 10 NAT IONAL ADVISORY I'D r" : ~~i ~~j ::i.~ m~ , 'iill" ~J:!1::; :!::,; .. ':i'!!E CO M MITT EE f ot AE RONAUTI CS ...- [Hi !I ljii" m:'·· L' .~; fur ' !::: n;:I: (]) ill ;l~i ',' ; 11 ;, ( 2 .1 2 ' , 1 l im I#.li ''[W;l!i L 11. 2 .. 1 J 11 f t, !:': T CII ' tl ~H 2 :." .. ,' ''' -;; ~ ': :n r .0 'i ~C Ie ' tr ' ill' o;:;tU c:...
~"j1i, 8,e 0 t a. "; ,, 1" 1 I 11 ' aJ I , :~ li!lffi!i:j::I !f!!l:: W(i , ~'" e ~.o f ib , C . 6.J :t T T Pr T I!liI :~: . .di~~;H! ~~,G: t·:· ~~: ;~ "'i' II I I 1 J I I 1 [" f-' Figure 22.- Aerodyn amic char ac t er is tic s of the NA CA 64A4l0 a irf o il secti o n, 24 -inch chor d ; TD T t e st 968 . ' •• •• • • •• • ••• • •• • • • • • • • • • • • • • • • • • ••• • • • • • • • • • • • ••• •• •••• •••• • ••• •• 2.8 .ll3; !---H I' I I I I I I I I I I I I I I I 1 I I I : 1-+ 1 :"'1... Jp. _ __ .. l lh 'L I I. 11 __ 1 I I t I I L I I I II I 0. 2Oc simul ated " pli t - .. ,," ' I I I V l 1 1 1' 1 I I 'I I T T I I I I I I I I I I I I I I I I 1 I flap de~lected 60 ~ ~:: I __ ' ~R I ' _ _ I I ~ L J .. 1. . .I .. J J L J.! L I .1.1 I .1 H+- 2 lli 'V 6 x 106 -;- I" r ~ . I --+ HH -"-'l- I I: I .. 1 1 V St andard{oughness,J ~+-~ - . - . 'f iT111 't"f"t 11 "1 T1 1 1 1 1 "1 1 1 1 T
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r'!' - I I 11 1 4++ 1 -1-" + I!tr J I :H--l l -f++- ~ F p+-- h+--l " I :;;; r ·w I "' l i-4"- f=l= 1 1 -- 1' I 1---+-- 1 1" 1 l I I 1 --1- • "[ '1 jr H-++f .. j-,-++ 1---+ •• ·d · • . . li .....
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H r- 11 1 '1 1 1 1 .1 1 J 6 10 ... ... I' ._ 1 __ I ~ :1 L 1 __ 1... 1 I H I t ': ... :_ NA T IONA L ADVISO ~~ T L' H I L L ! L ! !. ! ! 1 1 1 --L _ I :" ~ ,J l i l T ' I T I : J C ~MITIEE FOI AEROIIAUTl cs f ---- (j) ~ I I I . I I I I . + 2~ 4--- I -4;icii~n1~gtQ I or-tth6t-hH~~ I - H 11k I I --1 /1 1: F l h~ I ,' I "' ffl l~ ~ -- lr·~~~l . JtKI ' it~kM~kJ · laJI I H : T · Wf ~ ;~ : : qJ!;UI · 0 o I I I I I I I I I I I I I I I I I I I I I I I I l L. l I I I 1 1 II ' 1'1 I J Pil I J I I L ,+ LJ "" LI I I I J Ltd . L LJ LLl .....
Figure 23.- A erodynami c characteristics of the NACA 641A212 airfoil section, 24-inch chord, TDT test 953 .
•• •• •• • •• ., • •• • • •
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• • • • • • • • • • ••• ••• • • • • • • • • • •••• •••• ••• •• •••• • :> , 8 1 1
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_ S c 1 n a gi e 0 t a Ii ' ci ; 2 ~ +. 1+ 1. 6 _ ~ -2 . ' COMMITTEE FOR AlRONlUTICS 1---1- . 0 ,.' 1 =1 - F I~ t-- - b .1 8 I I J!~t 1 ~ ' 4- _, . __ tot , c e f c -e t .;r -r ~ ,! , - ~ I-' Fi g ure 24 .- Aerodynamic characteristics of the NACA 642A215 airfo i l s ection , 24-1nch chord ; TDT t est 959 .
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NACA bl.j - series and NACA 64A - series a irfoil sections of various cambers i n t h e smooth o 6 • c ondi tion and wi th standard leading - ed ge rou g hness . R, 6 x 10 I--' •• • • • ••• • •• • • • • •• • • • •• • • • • •• NACA RM No . L6JOl • • • •• • • • • •• • • • •••• bO • • • CI) • • • •• 'd • •••••• N AC A 6 4-ser i es (Ref . 1) ~ • • ......
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Airfoi l thic kn e s s , p erce n t of ch o rd Fi gu re 2 7.- Va ri atio n of lift - cu r ve slop e wi th ai rf oil t hi c k nes s ra tio fo r s om e NAC A 64 - s e ri es an d NACA 64A - s eri es a irf o il se cti on s of v arious camber s bo t h i n t he smoo th co ndit i on a nd w~th sta n d ar d '.
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