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NACA-RM-A51D25
Low-speed characteristics of a wing having 63 degrees sweepback and uniform cambe
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T18:37:27Z | |
| date available | 2017-09-04T18:37:27Z | |
| date copyright | 01/01/1951 | |
| date issued | 1951 | |
| identifier other | JNMCWDAAAAAAAAAA.pdf | |
| identifier uri | https://lib.yabesh.ir/std/handle/yse/219335 | |
| description abstract | INTRODUCTION Highly swept-back wings have been the subject of numerous investigations at low speed directed toward overcoming the longitudinal-stability difficulties encountered at moderate lift coefficients. Test results obtained on an untwisted, uncambered wing with the leading edge swept back 63 are presented in references 1 and 2. Further low-speed test results obtained on a wing of the same plan form but cambered and twisted to achieve a uniform lift distribution at a lift coefficient of 0.5 and a Mach number of 1.4 are reported in reference 3. These investigations indicated generally similar results in that large variations of the aerodynamic-center location were present for lift coefficients greater than about 0.3. These variations in aerodynamic-center location with lift coefficient were generally attributed to spanwise flow of the boundary layer and separation of the flow near the tip. The cambered and twisted wing used for the investigation reported in reference 3 was tested further with the outer half thickened in an attempt to increase the usable lift range and the results are presented in reference 4. This modification resulted in no changes in the longitudinal-stability characteristics of the wing. It was therefore concluded that the losses in lift near the wing tip and the consequent large variations in stability could be attributed almost entirely to spanwise flow of the boundary layer. It was reasoned that by utilizing camber alone, rather than camber and twist, the spanwise growth of the boundary layer might be delayed with a consequent delay in the onset of longitudinal stability changes to higher lift coefficients. In order to check this hypothesis it was decided to test a uniformly cambered wing with 63° sweepback of the leading edge and an aspect ratio of 3.5. This wing had an NACA 0010 base profile cambered for a lift coefficient of 1.0 on an a=0.8 (modified) mean camber line. This airfoil section was perpendicular to the leading edge of the wing. The results of tests in an Ames 7-by 10-foot wind tunnel of this wing at a Reynolds number of 3,700,000 based on the mean aerodynamic chord are reported herein. | |
| language | English | |
| title | NACA-RM-A51D25 | num |
| title | Low-speed characteristics of a wing having 63 degrees sweepback and uniform cambe | en |
| type | standard | |
| page | 20 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1951 | |
| contenttype | fulltext |
