| タイトル | Shock-dependent, thrust wings for supersonic flow |
| 著者（英） | Pittman, James L. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1993-01-01 |
| 言語 | eng |
| 内容記述 | A new wing concept which lowers the inviscid drag of a wing in supersonic flow is described. The thrust-wing concept uses a secondary shock that occurs to the rear of the maximum thickness location to produce a significant aerodynamic thrust force from the rearward portion of the wing, thus reducing the inviscid drag. The evaluation of the thrust-wing concept is conducted on a delta-wing planform of differing sweep angles and thicknesses at Mach 1.60 over a wide range of lifting conditions. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 93A23013
AIAA PAPER 93-0321 |
| 権利 | Copyright |
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