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NACA-RM-L6L27
Effects of a fuselage and various high-lift and stall-control flaps on aerodynamic characteristics in pitch of an NACA 64-series 40 degrees swept-back wing
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:56:32Z | |
| date available | 2017-09-04T17:56:32Z | |
| date copyright | 01/01/1947 | |
| date issued | 1947 | |
| identifier other | FMMCWDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;jsery=autho162s7D8308/handle/yse/179625 | |
| description abstract | INTRODUCTION The low-speed aerodynamic characteristics of a 40° swept-back wing of aspect ratio 4, taper ratio 0.625, and NACA 641-112 sections were reported in reference 1. This wing, like many swept-back wings, was longitudinally unstable at the stall because of wing-tip stalling and had relatively low values of maximum lift coefficient even with semispan split flaps, In an attempt to alleviate tip stalling and/or increase the maximum lift, tests have been made of the wing equipped with leading-edge flaps, outboard upper-surface flaps, and split flam hinged at the wing trailing edge. These tests were made at Reynolds number values of 3,040,000 and 6,840,000. In order to investigate the effect of a fuselage on the aerodynamic characteristics of the wing, tests have also been made of this wing with a fuselage in low, middle, and high positions. The tests were made to determine the characteristics in pitch at Reynolds number values of 3,040,000 and 8,090,000. | |
| language | English | |
| title | NACA-RM-L6L27 | num |
| title | Effects of a fuselage and various high-lift and stall-control flaps on aerodynamic characteristics in pitch of an NACA 64-series 40 degrees swept-back wing | en |
| type | standard | |
| page | 41 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1947 | |
| contenttype | fulltext |
