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NASA-CR-3449
Calculation of vortex lift effect for cambered wings by the suction analogy
Year: 1981
Abstract: An improved version of Woodward's chord plane aerodynamic panel method for subsonic and supersonic flow is developed for cambered wings exhibiting edge separated vortex flow, including those with leading edge vortex flaps. The exact relation between leading edge thrust and suction force in potential flow is derived. Instead of assuming the rotated suction force to be normal to wing surface at the leading edge, new orientation for the rotated suction force is determined through consideration of the momentum principle. The supersonic suction analogy method is improved by using an effective angle of attack defined through a semi-empirical method. Comparisons of predicted results with available data in subsonic and supersonic flow are presented.
Subject: ANGLE
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:29:02Z | |
| date available | 2017-09-04T15:29:02Z | |
| date copyright | 01/01/1981 | |
| date issued | 1981 | |
| identifier other | NWMKAEAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/30265 | |
| description abstract | An improved version of Woodward's chord plane aerodynamic panel method for subsonic and supersonic flow is developed for cambered wings exhibiting edge separated vortex flow, including those with leading edge vortex flaps. The exact relation between leading edge thrust and suction force in potential flow is derived. Instead of assuming the rotated suction force to be normal to wing surface at the leading edge, new orientation for the rotated suction force is determined through consideration of the momentum principle. The supersonic suction analogy method is improved by using an effective angle of attack defined through a semi-empirical method. Comparisons of predicted results with available data in subsonic and supersonic flow are presented. | |
| language | English | |
| title | NASA-CR-3449 | num |
| title | Calculation of vortex lift effect for cambered wings by the suction analogy | en |
| type | standard | |
| page | 86 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1981 | |
| contenttype | fulltext | |
| subject keywords | ANGLE | |
| subject keywords | ATTACK | |
| subject keywords | CAMBERED | |
| subject keywords | EDGE | |
| subject keywords | EQUATIONS | |
| subject keywords | FLAPS | |
| subject keywords | FLOW | |
| subject keywords | LEADING | |
| subject keywords | LIFT | |
| subject keywords | POTENTIAL | |
| subject keywords | SUBSONIC | |
| subject keywords | SUCTION | |
| subject keywords | SUPERSONIC | |
| subject keywords | THRUST | |
| subject keywords | VORTEX | |
| subject keywords | VORTICES | |
| subject keywords | WINGS |