| タイトル | Stability of 3D wing boundary layer on a SST configuration |
| 著者（英） | Parikh, P. G.; Bermingham, E.; Nagel, A. L.; Sullivan, P. P. |
| 著者所属（英） | Boeing Commercial Airplane Co. |
| 発行日 | 1989-01-01 |
| 言語 | eng |
| 内容記述 | Tollmien-Schlichting (TS) and cross-flow (CF) instability growth characteristics were studied in three dimensions, for the case of a Mach 2.4 SST with double-delta planform whose inboard leading-edge is subsonic and outboard leading-edge is supersonic. Attention is given to the requirements for supersonic speed laminarization of both highly swept, rounded leading-edge wings and moderately-swept, sharp leading-edge wings. Suction requirements for the control of both TS and CF instabilities are calculated; it is found that while mild suction and surface cooling are effective in TS-instability damping, the CF influence of such techniques is rather weak. CF instability control must be via pressure-distribution tailoring and suction. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 89A25031
AIAA PAPER 89-0036 |
| 権利 | Copyright |
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