NASA NACA-TR-718-1941 Pressure distribution over an NACA 23012 airfoil with a slotted and a split flap《带有开缝和分裂式襟翼的NACA 23012机翼上的压力分布》.pdf

《NASA NACA-TR-718-1941 Pressure distribution over an NACA 23012 airfoil with a slotted and a split flap《带有开缝和分裂式襟翼的NACA 23012机翼上的压力分布》.pdf》由会员分享，可在线阅读，更多相关《NASA NACA-TR-718-1941 Pressure distribution over an NACA 23012 airfoil with a slotted and a split flap《带有开缝和分裂式襟翼的NACA 23012机翼上的压力分布》.pdf（26页珍藏版）》请在麦多课文档分享上搜索。

1、REPORT No. 718.-DISTRIBUTIONOVER AN NACA 23021AIRFOILWITH A SLOTTEDAND ASPIJTFLU?slmfMARYBy THOMASA. HABBXSfind JOHN G. LowxtrA vreedieti”bution investigation ha% been con-ducte in the IVACA 4- 6oot ;M”cal un”ndtunnel todetemine the air loads on an iVACA 4?30$1 airfoil incombind”on with a 5Y6.66-per

2、cen but most of the load data for w it conformed to the NACA23021 airfoil profle and was constructed of laroinatedmahogmy with a hollow seotion to accommodate the . . .oopper pressure tuba. The baeio model, whioh eon-sieted of the airfoil in combination with a fuil-epanslotted flap (fig. 1), was fur

3、nished with a mahoganytiller bloc-kwhioh fitted the slot entry in the lower swface so that a smooth airfoil was formed. The slottedflap was attmhed to the airfoil by tww hinges looatedon the tips of the airfoil. The full+pan split tip wasconstructed of quartsr-inoh plywood and was attachedto the air

4、foil by several braces equally spaced alongthe span.The full-pan slotted flap (0 -ie . . .c% =/.33Mm-hm WNAOAtiMti aOMltrdetWk. FIspsfit- “d - ;6.“ “- “.-=.- .: .!.,.= ,=. d. .“-. ,=_ . - . ._.;._- - .-=.-: =- - ., .-6 - U)per surftice-_-.i:_ -=+,.1PJ,CU.=2!55.-FICUBE19.-PrmuMdtsMutbn an t-t-d.-4:-:

5、-i-,L.,.i, :t;,i, P)UH7 0/4+/!- Aihbil WMI f?op, -15”- . . ,- “30”- - . . .-45”(b) Attbmmeuwlmaf-, aw-lsI, .“ :IProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I: ,. ,“ 1 .!,I:. ,11 I,.; , .,. 1: , , , I, ,!, ,. , IProvided by IHSNot for ResaleNo rep

6、roduction or networking permitted without license from IHS-,-,-1 1. I I I I I I I I I I I i L I I1, 1 m. -1 1 1, ,.“.: ”,:“ !: :.1 ,;l, ,. .:, I”.:!.;:; .:-j “1 -. .Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I I I I*-L. . . . +!.-J”Hiiii”+tl+t i

7、 i“ i i i i L 8R5t 1 Ithat k, theforce acting parallel to the flap referenoe line is direotadforward. The magnitude of these foroes is greaterihan for the NACA 23012 airfoil-flap combination(reference 3). Jn the mhmlation of the rwltent forcem the slotted flap, the ohord foroee should be taken intoM

8、Oouut but it should be remembered that these foroea10 not include akin friotion.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-266 REPORT NO. 71 - ,., , .,.1.?.8.4.5.6.7.s.9.10.11.,. “ . . . .lZKFBItENCES ; ,_ . ., ”Wepdnger, Csri J., mad H- Thomas

9、A.: Wii NACA,. . . .K”Wallace, RudoW Inwstigaticm of FuL&xde SpIit Trailh)g-Edge. Wtng Fiaps with Various Church al!d Hinge kIdom. Rep. No. 589, NACA, 1.985.Wanzing, Carl J.: Pressure DMbution over a Clark Y-H “”AfrfoU Seotion with a Split F1ap. T. N. No. &, NACA,lfi.Wenzinger, CM J., and Harria, Th

10、omaE A.: Premuru DIs-trfhutlon over a Iteotaogular Airfoil wfth a Partial-SpanSt F18p. kp. No. 871, NACA, 1886.Wenzbger, Carl J.: Prwure IMrfbution over an N. A. d. A.23UI?4AidoiI-ivith an N.”A. C. A. 28012 )ikternal-Atrfoip. kp. No. 614, NAC& 1988.Wensinger, Carl J., and Hairis,. Thomaa A.: The Vcr

11、tioalWind Tunnel of the Natknud Adv!sory Commit& forAeronautics. Rep. No. 867, NACA 1981._ William (1., and &a, Milton B., Jr.: Pmaum- “ Distribution Investigation of an N. A. C. L 0002 Mrfoflwith a 50-Percent-Chord Plain Flap and Thtwe “T.T. N. No: 784 NACA, 1989,Wermfnger, Cad J., and HarrfE, Thomaa A.:”Wfnd-Tunuel -”-.tid% of a! N. L C. A. 23012MM with VariOUBArrangement of Slotted Flspa Rep. No. 664, .NACA,1989. .Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-