NASA NACA-RM-L7A30-1947 Wind-tunnel investigation of air loads over a double slotted flap on the NACA 65(216)-215 a = 0 8 airfoil section《NACA 65(216)-215 a = 0 8翼剖面上双开缝襟翼空气荷载的风洞研究.pdf

《NASA NACA-RM-L7A30-1947 Wind-tunnel investigation of air loads over a double slotted flap on the NACA 65(216)-215 a = 0 8 airfoil section《NACA 65(216)-215 a = 0 8翼剖面上双开缝襟翼空气荷载的风洞研究.pdf》由会员分享，可在线阅读，更多相关《NASA NACA-RM-L7A30-1947 Wind-tunnel investigation of air loads over a double slotted flap on the NACA 65(216)-215 a = 0 8 airfoil section《NACA 65(216)-215 a = 0 8翼剖面上双开缝襟翼空气荷载的风洞研究.pdf（21页珍藏版）》请在麦多课文档分享上搜索。

1、RESEARCH MEMORANDUM WIND-TUNNEL INVESTIGATION OF AIR LOADS OVER A DOUBLE SLOTTED FLAP ON THE NACA 65( 216) -215, a = 0.8 AIRFOIL SECTION Bs Fioravante Visconti Langley Memorial Aeronautical Laboratory Langley Field, Va. NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS WASHINGTON April 9, 1947 Provided by

2、 IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MC. RM NO. 730 NATIONAL AIXJSORY COMKC FOR l;hinktioJ and d.tuble slottatim along the chord Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-4 a NACA RM Nos L7A30 P

3、 normalpressure coefficent (p/%) U 0 airfoil section mgle of attLckj degrees flap deflection wfth respect to airfdl chord, degrees, % ponitive- when trailing edge of flap is doflectod downward R Reynolds number The modal waB an MACA 69(216) -2.215, a = 0.8 airfoil eection equipped with a double slot

4、ted flep %I.i;ed at.0.043 cnord from the flap leading edge and 0.020 chord bolow the flap chord line. “ - “ “ Teete wore conducted at flap deflections of Oo, 25*, 30, 35, h0, XIo, 55O, and 70 Air loads were detsrmined frcm neasureaents of surface pressures over .tho whg Hection, vtmg and flap primri

5、ly at a Reynold8 num5er of 6.3 X lo6. The air lca and in genera., the maxirmun loda for any particular flap doflectim may ocsur sk any section noml-f orce vahe begmd 1.4. No mifo-m variation of these air 1oad.s could be expocted due to %he ra3Lcal changes of air flm through the slot8 a8 the fl20 16.

6、40 21 .lo6 1z :E; NATIONAL ADVISORY COMMITTEE. FOR AERONAUTICS $ r 8 . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . . . . . . . *- . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . . - . .

7、. . . .- Vane -1 70 55 I . . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Flg. 4 NACA =No. L7A30 L B P B P B Provided by IHSNot for ResaleNo reproduc

8、tion or networking permitted without license from IHS-,-,-NACA RM No. L7A30 Fig. 5 2.0 k“ 1.6 B rl rl 2 1.2 0 I $ .8 a 2 .4 f rl I a N*T$itN! rns0RY - tllEE Fa AEMNAUTKS 0 IIIII, 0 .4 .8 1.2 1.6 2.0 2.4 2.8 32 3.6 Section normal-force ooefficlsnt. on Provided by IHSNot for ResaleNo reproduction or n

9、etworking permitted without license from IHS-,-,-Fig. 6 NACA RM No. L7A30 Figure 6 .- Variation of normal-foros ocaffioisnts with flap deflsotion of an NACA 65(216)-2l5, a = 0.8 airfoil section apulppsd ulth a double slotted flag. R= 6.3 X lo6. Provided by IHSNot for ResaleNo reproduction or network

10、ing permitted without license from IHS-,-,-NACA RM No. L7A30 Flap deflection, 6, , dag Figure 7 .- Variation of rnaxlmun normal-foPae ooerfioients rlth rl* ddleotion of an HACA 65.(216)a5, a = 0.8 alrfoll section equlpped with a double slotted flap. k6.j X lo6. mg. 7 Provided by IHSNot for ResaleNo

11、reproduction or networking permitted without license from IHS-,-,-2.8 E 2.4 p U 8 5: 2.0 rl 91 1.6 0 .-I Y 1.2 0 rl B - .a i .4 0 -;r4 -16 -8 0 a 16 Saotion angle of attack, a. , dag Seation noddoroe owffiolaut, on 3 Provided by IHSNot for ResaleNo reproduction or networking permitted without licens

12、e from IHS-,-,-. NACA RM No. L7A30 Fig. 9 1 e I 9 B 0 0 B 1 1.0 P B n “. 0 -4 .a 1.2 1.6 2.0 .4 2.8 3-2 Seotlon nomsl4oroe ooaffioiant, on igt-8 9.- %ah effect on vnna oh.rsota*tica of the BffiA 65(U6)-215, L = 0.8 alrfoll seotlon equipped with a double alotted flap. = 35. Provided by IHSNot for Res

13、aleNo reproduction or networking permitted without license from IHS-,-,-Fig. 10 NACA RM No. L7A30 .1 0 Figure 10 - Scale effeot on flap characteristic8 of the NACA 65(u6)-21 a = 0.4 airfoil section equipped with a double slotted flag. 6f = 35”. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM No. L7A30 Fig. ,ll Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-