NASA NACA-RM-A7L11-1948 Low-speed investigation of a small triangular wing of aspect ratio 2 0 II flaps on flat-plate models《展弦比为2 0的小型三角形机翼的低速研究 II 平坦飞机模型的襟翼》.pdf

《NASA NACA-RM-A7L11-1948 Low-speed investigation of a small triangular wing of aspect ratio 2 0 II flaps on flat-plate models《展弦比为2 0的小型三角形机翼的低速研究 II 平坦飞机模型的襟翼》.pdf》由会员分享，可在线阅读，更多相关《NASA NACA-RM-A7L11-1948 Low-speed investigation of a small triangular wing of aspect ratio 2 0 II flaps on flat-plate models《展弦比为2 0的小型三角形机翼的低速研究 II 平坦飞机模型的襟翼》.pdf（20页珍藏版）》请在麦多课文档分享上搜索。

1、LOW-SPEED INVESTIGATION OF A SMALL TRIANGULAR WING OF ASPECT RATIO 2.0. II - FLAPS I ON FLAT-PLATE MODELS By Leonard M. Rose CLASSTF?C? T10P.J CHANGEp Aeronaut cal Laboratory . V“ . -. . NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS Provided by IHSNot for ResaleNo reproduction or networking permitted

2、without license from IHS-,-,-ERRATUM NACA RM No. A7IU The title an the cover should read: instead of: Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-By Leonard M. Rose Low-speed wind-tunnel tests were made aP flat-plate wings ares applied to the dat

3、a were the 881p as those wed in refereme 2. No additional corrections were made to account for the deflection of the plates. As was tlie cam for the previous testa, the data were obtained at a Reynolds nuniber of approximately 1.8 x loe, baaed on the wing mean aerodynamic chord. L Provided by IHSNot

4、 for ResaleNo reproduction or networking permitted without license from IHS-,-,-KACA RM No. A7Ll.l 3 The pitching Itlomanta are presented about an axis in the plane of the wing perpendiculax to the air stream, This axis 1s 18 inches aft of the vertex and passes through the 25percerrt point of the me

5、an aero-c chord of the triangular models and the 15.hercerrt point of the mean aerodymmic chord of We del with a swept-back trailing edge, (see fig, 2,) The data are presented in the form of stadard NACA coefficients which are defimd as follows: CL lift coeff icient V airdtream velocity, feet per se

6、cond S wing ares, quare feet C mean aerodynamic chord of the wing, feet - P mass density of air, slugs per cubic-cfoot CL angle of attack, degree8 s flap deflection about hinge line, degrees .I Flat-plate models afforded the shplest mans for studying the fhp pk fo whereas the values herein were dete

7、rmined by the ratio of a0,ddS to %laat; thus, Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-6 _y- NACA RM Wo. An11 would be obtained on other models having similar plan forme and aspect ratios. A constant-chord flap was found to be the meet effecti

8、ve and a skewed-tip flap the least effective. In general, the results indicated that the effectiveness of both the split and plain flaps was reduce, I . . . . . . b . . . . . . . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-WA RM No. Apll I I I I 1 I I 60 70 80 90 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-,-,-