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NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS

WARTIME REPORT January 1S*1 u

Advance Ccof idenUal Depart

OHMHMBI or HACA WKXJB sans OTCWBOOXAB *D

TAPERSD MBTOnS, WCtODIHG IB EFFECT OF SPUT HAPS

x\r Barry Greenberg

Lengley Manorial Aeronautical Laboratory Langley Field, Ta.

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NACA

NACA WARTIME REPORTS »re reprint« of papers originally Issued tu provide rapid distribution of sdvsnre research results to an authorized group requiring them for the war effort. They were pre- viously held under s security status but are BOW unclassified. Son* of these reports were not tech- nically ««ted. All have been repraducedj^geQ^ayr^order ta espedlte general distribution

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.: CH-BASTESIsilCS 0» «ACA 44008 fSBXXS RSCIASTOIIB A?D

t^iin AiBtoii«. unrasn «1» »WOT 0* »lit »*«•

By Harry Oreanterg

XXIBOBUOTXOB

.

»t the reqr.eei of tae InttM o.* Aeronautic«, Bawjr t«rarta«r.r , teat« war« aade In the vsriable-den»itjr wind tunnel of a tarurjA »in« of 3-iC-iB plan for« aad haaed «a too FACA 44008 eerlae »«etIon« 'reference 1). The vine wa« also teated -ltt 0.8 chord »flit flat;», deflected 60°, Is the ceuter of t ..o wing and hawing flat; «pan to «lag apan ratloa of 0.3t C5, 0.7« aad 1,0, reapeotlweX'. Xa ordar to cat data froa which to calculate tha eharaeterle- tie« of tha flapped wing, the lnreetigatlon of rafaraaea X ttt ext untied to include taata of the four rectangular •• alrfolXa of the SAO* 4400B aarle« (440SB. 44X88. 441SB, aad 44X88) with faXX-epaa 0.8 e'acrd, tralllag-edge «pltt flap« deflected öC° •

SCSSI3 ACT TZSTS

The nur.ber» la the dcsigaatloa of the tapered wlag (3-10-16) refer to taptr ratio, aspect ratio, aad root aeetlon pcrceat thlehneea. reap to t lval»." ' the construction tip aeetloa w«a S percent thlek. The wing waa constructed vain* «tra'.ght-llne eXe:.enta between correopondltp polata oa t..i root (5ACA 441bB) and VI« (Si<5A 440S8) aaetloaa. and «o that la front «lernt Ion the upper eleuent waa a otraicht lit.« froa 11; to tip (".. . X). All the aodaXa had a ring area o* loG aquare lne'nea. were oade of alaalaw alia}-, and'BRd no geonctrle tvlet.

reaauren-cat« of lift, drag, cad pitching moment were r-sde lc the v»rl*hla-denelt]r wiüd tunnel According to • tnudard procedure (ref er*-.;ce 8? .-*. a ta«t Beynold» num- ber of approximately J.C3C,CC3, which correspond« to en «ffestiwe Bcynolte anmber ?« of approximately 6.COO,000 (reference 5).

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Standard piote enowta* the eaarecterlBtiCi ef the rectar.e»i-r airfoils rith C.S chord split flaps deflected dO« are shown Is figure» 8 to ä. Tat «setion cbarn-ter- latlce after tu* »toll are cot a'ae-a. r-o jr!..«-';«. eaar- «ctriif.oi ara sa*ta*rls«4 in table ;.

5be characteristics of tu» tapered r'.r.f with t --• dif fereat flap sr»n4e'..«.ti are shown In figures 6 to 10« Xa future o, a calculated curve ef fls#. deter.-.in«' 1/

toe .-.ethod of refer»aca 4, la «Iwes for CO*parieon <-ith tue teat results.

Values «f c=<le of «ere lift also w«r« calculated toy the eetaod of reference S aad »h#w £0*d ««reesent »itfc •ensured value* >i shorn is te'ale XX. She lift-curve olopo «aa calculated (refercaee 4) for tae plain *is$ eat not for the «lufta .-ft», flape bseauee. tie olopee of the »ecttoae with f la-e era far free conatar.t. The aösieat about the aerodyaauic eeater of tee plal- rln$ was calculated by the elapler .t'iod o' reference 6 rhiea assucee cne.c. is constant elos«* the epes. The (soKOnte for the -l-gs with flaps deflected were obtMr.ed a? the metnod of reference ft «ein« avert«-* value* cf the section conent coefficient for CSQ *I-,i •**'»*' veinee jf «c^ at a lift coefficient of 1.0 for the flapped j-. rtJar of tae t,an.

Xa the caleulatloa of r-xir.'m lift by the scthod ef reference *, the open !•>**. ülatr! eitlen -at obtained ty the -eico-i of TtftTn.*» -. Jood agreement with exrencent le s'-c-n for tae plaic rir.fr c.-. poor ecreecent for the wlnr with full-spaa flop. Xa fret, the measured aericum lift of :":.* tiered flapped rln§ 1« higher than that of aa7 of the flapped sections t£e)Bj the span. The dlocrep- ascy ie attributed to the -.««ecus,- of . .te at-ni-virt iens involved In t..e calculation of i.a.-!•-".:. lift. C..r»e ' : 1- culetloas were not ~u.f* for the rjU**» with partial-spaa flape in view of t<.e : bore and ir. view of the =di»d uc- certriety of t-e weise of the eertlon : axi:-.ua lift devel- oped near the flap end. Xc an." case, tae reeanred -.-„lues of aexlaua lift coefficient of tx.ee« tveexed Tlr^a aay not be attainable la fli.ht d-.e to tae lateral lna»afeillt* associated -iti. tip ntailir« before "he ar.fle ccrrespond- lns to saria-un lift ean be reached (reference ")•

lassie.- y «aortal Aeronautical T.ororitory. r*t local Advisory jo-aaltt.e for Aeronaut lea,

la-»ley field. *a.

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1. Hill—»> Albeit; I ro.'t.:-.;.-; ".a-crt on t;i Caaracter- latloa o-T tue ".A.C.*. 44C.0R Serial Alr'oilb. liAS.k L02, .:-ro-i 1939.

2. u'r.cocB, £IB* ra "., ar.i Abbott, Ira I.I The 5.A.C.A. Var'.atle -i'ena* t] Sind T'Jtir.el. Ret. >" >. 41c, "ACA, 1933.

3. ;-T I :j. ?.-..'• ., :. "., an- S ••.;••• a, Albert: Airfoil Sec- tion Qbarftctaristloi &• »ffeeted t; Varietione of tile Revolt's "urber. ?.ep. To. o3ö. KA'JA, 153".

4. Ai.dergon, Raymond ?. : Ine E»i e/'.aienial and Calcule* ed C-^rai- ter' a tics of 28 Tar »red .<lngs Sap To. 62?, XAQA, 1-3E.

b. fenrio i, near; A., ar.l «ndarsor., Eajsos-i ?.: Calcula- tion of «erortynf.mie Characteriseis» of T-irered »Inga with Fartful-Sian ?lop«. Eep . to. oit, .J.-.CA, 1939.

6. Fearaon, E. A.: 3yan Load Distribution for lacered flare wUi. partial-Span 31ape. Pap. So. 585, «ACA. 1937.

7. Faroes, Castran '.'•: (aparad Sinjs, Tip Stalling, and Fraliclv.ry Rezvlts froc. Ttat» of t.ie Stall-Control I lap. IVOi -iCR, :*v. 19?7.

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IB e.i»i -16.U -.272 .9 3 -17.1« .095

These val'iof troly to u lineur lift curve approxiimtlcf, the ox-ir!- üK-ntol lift BUTT*.

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TITLE: Characteristics of NACA 4400R Series Rectangular and Tapered Airfoils, Includ- ing The Effect of Split Flaps

AUTHOR(S): Greenberg, H. ORIGINATING AGENCY: National Advisory Committee for Aeronautics, Washington, P.C.

ÄTTD» 8344

OQIO. AOINCT MO. ACR-L-493

Jan '41 U.S. V"" _15- IUUSTU110NS

tables, graphs, drws ABSTRACT:

?*• I Tests were made in variable-density wind tunnel with the tapered wing tested with 0.2 chord split flaps deflected 60° in center of wing with flap span to wing span ratios of 0.3, 0.5, 0.7, and 1.0, respectively. Rectangular airfoils were tested with full-span 0.2 chord trailing-edge split flaps deflecting 60°. Standard plots are presented which show characteristics of airfoils tested. Principal characteristics are summarized in table form. Corresponding calculated results are given for some characteristics.

DISTRIBUTION: Request copies of this report only fr. DIVISION: Aerodynamics (2) SECTION: Wings and Airfoils <6) ATI SHEET NO.: R-2-6-5J

Air Motorlol Command U.S. Air Ferco <X*.-yl -:

AI El TElnnr*<

I TITLE: Characteristics of NACA 4400R Series Rectangular and Tapered Airfoils, Includ-

ing The Effect of Split Flaps AUTHOR(S): Greenberg, H. ORIGINATING AGENCY: National Advisory Committee for Aeronautics, Washington, P.C.

ßTO- 8344

OfilO. AOCMCY NO.

ACR-L-493

*>" '41 Ilnrlaaa U.S. uurav BI PAOES

15 UUBTOATlOttJ

tables, graphs, drwes

Tests were made in variable-density wind tunnel with the tapered wing tested with 0.2 chord split flaps deflected 60° in center of wing with flap span to wing span ratios of 0.3, 0.5, 0.7, and 1.0, respectively. Rectangular airfoils were tested with full-span 0.2 chord tralllng-edge split flaps deflecting 60°. Standard plots are presented which show characteristics of airfoils tested. Principal characteristics are summarized in table form. Corresponding calculated results are given for some characteristics.

DISTRIBUTION: Request copies of this report only from Originating Agency DIVISION: Aerodynamics (2) SECTION: Wings and Airfoils (6) ATI SHEET NO.: R-2-6-gs

SUBJECT HEADINGS: Wings - Aerodynamics (99150); Flaps, Wing - Lift and drag characteristics (37550)

Air Motor iol Command U.S. Air Forco

AIQ TECHNICAL INDEX Wright-Pattorson Air Forco Dose Dayton, Ohio