درباره ما
NACA-RM-A52K20
Pressure distribution at Mach numbers up to 0.90 on a cambered and twisted wing having 40 degrees of sweepback and an aspect ratio of 10, including the effects of fences
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T18:13:35Z | |
| date available | 2017-09-04T18:13:35Z | |
| date copyright | 01/01/1953 | |
| date issued | 1953 | |
| identifier other | HFMCWDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;jsery=autho162s7D8308/handle/yse/196568 | |
| description abstract | INTRODUCTION A semispan model of a high-aspect-ratio swept wing in combination with a fuselage of high fineness ratio has been tested in the Ames 12-foot pressure wind tunnel. The wing was cambered and twisted, had 40° of sweepback, and an aspect ratio of 10. The results of measurements of the forces and moments on the wing alone, on the fuselage alone, and on the wing-fuselage combination have been presented in reference 1. The results of pressure-distribution measurements at nine semispan stations of the wing, alone and in the presence of the fuselage, are presented in the present report. Pressure data are also included for the wing with three upper-surface fences and with four upper-surface fences. | |
| language | English | |
| title | NACA-RM-A52K20 | num |
| title | Pressure distribution at Mach numbers up to 0.90 on a cambered and twisted wing having 40 degrees of sweepback and an aspect ratio of 10, including the effects of fences | en |
| type | standard | |
| page | 135 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1953 | |
| contenttype | fulltext |
