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NASA-CR-166426
New considerations on scale extrapolation of wing pressure distributions affected by transonic shock-induced separations
Year: 1983
Abstract: Use of this analytical parameter, it is shown, highlights the distinction between cases which are dominated by trailing-edge separation, and those for which separation at the shock foot is dominant. Use of the analytical parameter and the distinction noted above greatly improves the correlation of separation data and the extrapolation of wind tunnel data to flight conditions.
Subject: PRESSURE DISTRIBUTION
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:49:44Z | |
| date available | 2017-09-04T16:49:44Z | |
| date copyright | 01/01/1983 | |
| date issued | 1983 | |
| identifier other | BUHOEEAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/113313 | |
| description abstract | Use of this analytical parameter, it is shown, highlights the distinction between cases which are dominated by trailing-edge separation, and those for which separation at the shock foot is dominant. Use of the analytical parameter and the distinction noted above greatly improves the correlation of separation data and the extrapolation of wind tunnel data to flight conditions. | |
| language | English | |
| title | NASA-CR-166426 | num |
| title | New considerations on scale extrapolation of wing pressure distributions affected by transonic shock-induced separations | en |
| type | standard | |
| page | 63 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1983 | |
| contenttype | fulltext | |
| subject keywords | PRESSURE DISTRIBUTION | |
| subject keywords | SHOCK TESTS | |
| subject keywords | TRAILING EDGES | |
| subject keywords | TRANSONIC FLOW | |
| subject keywords | WIND TUNNEL TESTS | |
| subject keywords | WINGS |