1、, . .II.“m E- r. .* .:” / / -5:-.:.;:,.“ .-:,., -.: . . ,-,-NATIONAL ADVISORY COMMITTEE FOR AERONAlilCS.c./Tf :;,WAlrmm lUIPOIU!ORIGINALLY ISSUEDJanuary 1943 asAdvance Restricted ReportTD.mEL sTIGATI OF cjOL-mAE WcIsTIcsXII - VARIOUS COVER-PLATE ALINEMENTS TEENACA 0015 AIRFOIL WITH A 30-PERCENT-CHOR
2、DFLAP AND LARGE SEALED INTERNAL BALANCEBy H. Page Hoggard, Jr.Langley Memorial Aeronautical LaboratoryLangley Field, Va. FOR FwE:wi:3”ii -” -.MM W) BETAMN TM)?.+?H!3ROOMWASHINGTONNACA WARTIME REPORTS arereprintsofpapersoriginallyissuedtoproviderapiddistributionofadvanceresearchresultstQ.anauthorized
3、grouprequiringthemforthewareffort.Theywerepre-viouslyheldunderasecuritystatusbutsrenowunclassified.Someofthesereportswerenottech-nicallyedited.Allhavebeen-reproducedwithoutchangeinordertoexpeditegeneraldistribution.L- 511/-,-.+Provided by IHSNot for ResaleNo reproduction or networking permitted with
4、out license from IHS-,-,- 13 1176013639647 ;.,-.-. NATIONAL .4i)VISORYCOi4MITTEE IOR AERONAUTICS-. -WIND-TUNITEL INVEST IGATIO?T F COTROJIYifTSON THEA NACA 0015 AIRJ?311:WITH A 3 thsrlative values , however , should be practically indepnd-Pnt of tunnl effect. Th incrmnnts of drag coefficient(fig. 13
5、) were determined by deducting the drag coPffi-cierlt of the airfoil with plain 0.30c flap with sea.ld gap,flap not deflected, from the drag coefficient of the airfoilwith the covr plates bent to the various positions and theflap neutral.The increments of minimum profil-dra coefficient areplotted ag
6、ainst chan:es in vnt width in figure 13+ %!ndingtshe platp in at either bend location had no iasurableeffect on the minimum profile drag, BendinR th plats outgave an increcse in dra which .ncreaspd rapidly with thelarger amounts of befl, The 0,G3c beil(llocation save largerincremnts of drag for the
7、ss.me vent width than th 0,50cbend location. ThP larger incremn.ts of drag may be attrib-uted to the spoiling of th air flow vr th flap by theprotruding plate which acts lik a spailr, Th spoilr action indicats that the incremnt of drag produced is afunction of th= angle %etweeri t?e rotruding part o
8、f theplate and the airfoil surface anti Increas?s as thp angle .increc.ses, .CONCLUSIONSTh rqults of the tests indicate th- fellowing con-clusions :1. Manufacturing im:p-rfection in the alinmnt of thecover plates for internally balanced flaps with the airfoilcontour , if largp , may hav serious ffer
9、ts cn the resul-tant hinge moment of a.flap with a s?a,led int.ern$!.lbrilance.2* In Fenpral, bending the cover pl?.tes in or outincreased th negative slope of curvs of flap hinge moment.,ttd against ,nglc of attack and against flap deflection,.,?, A rudder with interna,l balance with the coverplate
10、s lent out an algrciabl nt.ount should have a tpn-dency toward rudder lock in a sideslip, Similarly, anelevator should hs,ve a tendency toward overbalance whnused in the lading attitude Whet the ccvf?r plates arbent out. Ben,ding th plates in should hav no serious eff-et other than a slight incrr+as
11、e in hing moment.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-1.14.4. Bending the cover plates in or out had practicallyno effect on the slope of the lift curve fol” the airfoil,5. The lift effectiveness of the flap with flap de-flection and angle
12、 of attack of like sign was reduced whentle cover plates were bent out at eithpr bend location,13ending the plates in did not affect “tilelift effective-ness,6. The incr?ment of miitiUm profil drag dll to bend-ing the plates out was appreciable and was larger when thebegd location was near tle cover
13、-Plate trailing edgeOWithin t:e experimental accuacy of the tests, bending thecover plates in had no RpprPcia%l.e efiect on the minimumprofile-drag cofficiont.Langley Memorial -4erona.uticnl Laboratory,National Advisory Committee for Aeronautics,. Langley Field, Va.,*.Rl?O?3HiIlNCES1. spars, Aichard
14、 I, and Hogga,rd, H, pae, Jro: WindTunnel Investigation of Control-Surface Characteris-tics. XI - Various Large Overhang and Internal-TypeAerodynamic Salancfis for a Straight-Contour l?lap onthe NACA 0015 Airfoil. iiACA A.R,R., Jan, 1943,2, Hoggard, H. Page, Jr.: Vj.nd-Tunnel Investigation ofControl
15、-Surface Characteristics, X - A 30-Percent-Chord Plain Flap with Straight Contour on the NACA0015 Airfoil. NACA A.H.R, Sept. 1942,3, Wenzingfir, Carl J, , and Haris, Thomas A.; The VerticalWind Tunnpl of the Nati onal Advisory Committee forAeronautics. ReP. No. 387, NACA, 1931.d,Provided by IHSNot f
16、or ResaleNo reproduction or networking permitted without license from IHS-,-,-12.TA33E IORDINATES FOR NAC!A 0015 AIRFOIL WITH STRASGHT-COTTCUR FLAP ,rStations and ordinates in percent of airfoil chord 1L- . . Station-01.252.55.0?.510152C2530o506070839095100100-.Uppersurface-o2.373.274.445.255.:;t“ -
17、Xo bend50Go250636363636363!-ChanS13invent width,(frtionof chord)0.0000-OOOPG.0052.0078-.0026.-.ooljoo3.0026.0052.0978-1, da.-.( jc1-0.53_. )$-*5:-.54_*54-p+-.54-.56-,54“a-*Y/$ Ch -)(X b(zkwc,-cover plofe, benf ohf; bend location, W; vent Wih,0.0130 c-Provided by IHSNot for ResaleNo reproduction or n
18、etworking permitted without license from IHS-,-,-* . . . .-. . -,L-5111SIRiibProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. .* . .“. . . L-511i?14mlll Hll m-1-tta71a77a13 I 1,% ;- 1, iI ,_p”llliI I I Ib“+ljfl-ii.iiiiiiiiiiii.jfProvided by IHSNot f
19、or ResaleNo reproduction or networking permitted without license from IHS-,-,-.,.ACA *(. ,.,4 :- .u 4 /- t,-,Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . . . . . rs511CQProvided by IHSNot for ResaleNo reproduction or networking permitted witho
20、ut license from IHS-,-,-Am,b . I - 1 148/i I I 1 , , , , II I I I 17 I-F“YI r I , I 1 I I I 1 1 1 I 1 1 I 11?.014 %?4 h ,8 10 12 1# 16(“ Airb/ aecfon Iff coefficim(cz “figure 10.- Secflon aermnamic churacfenbfics of an NACA 00/5 ojoifop, Q30c straighi conour;bokwwea050+”/W/igap,sealed!cover plale, b
21、ent OU; bend /ocafion, Qt33 c ; veni wdlh,QOIWC.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-1+l-lm24.0816-12111111111.1.4 12 10 :8 76 :4 :2 0 .2 .4 .6 .8 1.0 12 14 16. *M Y bu/unce, Q50c hernd;fgop;sealedi cover pat!ej ben oukbenolocdion, 0.63c ;
22、ven W184130cProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- . . . . L-511#I I l I I I I1 I :Ucm / 8 1 /uGcx/f,wr#j - 0.50C-2 .d3 .CA4 .0/35 .0t!6 .0A7 .dwF/gure 12. - Voria+ion of +% f/2zp hnge -momsd pxamders VW% ckn ea:$:,ven Q.0 - “ + + - - -1 ,$
23、 Ib $ .0;5 .006 .0;7 L&FIgue - Vardon of the incr-ement of mlhimum pro fik-o!.og coeffielenfwih than e in vemf widf+& Cover plu +esebed at each of +WO Y-Iocahons. A?ACA 0015 o.Ihfoi/ wfb Q 0.30c skzlghf- coniour f/p hawhg +a 0.50cf in/e777al baiance.GProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-
