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NASA-TR-R-428
Extension of leading-edge-suction analogy to wings with separated flow around the side edges at subsonic speeds
Year: 1974
Abstract: A method for determining the lift, drag, and pitching moment for wings which have separated flow at the leading and side edges with subsequently reattached flow downstream and inboard is presented. Limiting values of the contribution to lift of the side-edge reattached flow are determined for rectangular wings. The general behavior of this contribution is computed for rectangular, cropped-delta, cropped-diamond, and cropped-arrow wings. Comparisons of the results of the method and experiment indicate reasonably good correlation of the lift, drag, and pitching moment for a wide planform range. The agreement of the method with experiment was as good as, or better than, that obtained by other methods. The procedure is computerized and is available from COSMIC as NASA Langley computer program A0313.
Subject: AERODYNAMIC
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T18:48:25Z | |
| date available | 2017-09-04T18:48:25Z | |
| date copyright | 01/01/1974 | |
| date issued | 1974 | |
| identifier other | KOWWAEAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std/handle/yse/229726 | |
| description abstract | A method for determining the lift, drag, and pitching moment for wings which have separated flow at the leading and side edges with subsequently reattached flow downstream and inboard is presented. Limiting values of the contribution to lift of the side-edge reattached flow are determined for rectangular wings. The general behavior of this contribution is computed for rectangular, cropped-delta, cropped-diamond, and cropped-arrow wings. Comparisons of the results of the method and experiment indicate reasonably good correlation of the lift, drag, and pitching moment for a wide planform range. The agreement of the method with experiment was as good as, or better than, that obtained by other methods. The procedure is computerized and is available from COSMIC as NASA Langley computer program A0313. | |
| language | English | |
| title | NASA-TR-R-428 | num |
| title | Extension of leading-edge-suction analogy to wings with separated flow around the side edges at subsonic speeds | en |
| type | standard | |
| page | 73 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1974 | |
| contenttype | fulltext | |
| subject keywords | AERODYNAMIC | |
| subject keywords | BOUNDARY | |
| subject keywords | CHARACTERISTICS | |
| subject keywords | COEFFICIENTS | |
| subject keywords | CONTROL | |
| subject keywords | EDGES | |
| subject keywords | FLIGHT | |
| subject keywords | FLOW | |
| subject keywords | LAYER | |
| subject keywords | LEADING | |
| subject keywords | REATTACHED | |
| subject keywords | RECTANGULAR | |
| subject keywords | SEPARATION | |
| subject keywords | SPEED | |
| subject keywords | SUBSONIC | |
| subject keywords | WINGS |