| タイトル | Aerodynamic configuration design using response surface methodology analysis |
| 著者（英） | Lepsch, Roger A.; Stanley, Douglas O.; Engelund, Walter C.; Unal, Resit; Mcmillin, Mark M. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1993-08-01 |
| 言語 | eng |
| 内容記述 | An investigation has been conducted to determine a set of optimal design parameters for a single-stage-to-orbit reentry vehicle. Several configuration geometry parameters which had a large impact on the entry vehicle flying characteristics were selected as design variables: the fuselage fineness ratio, the nose to body length ratio, the nose camber value, the wing planform area scale factor, and the wing location. The optimal geometry parameter values were chosen using a response surface methodology (RSM) technique which allowed for a minimum dry weight configuration design that met a set of aerodynamic performance constraints on the landing speed, and on the subsonic, supersonic, and hypersonic trim and stability levels. The RSM technique utilized, specifically the central composite design method, is presented, along with the general vehicle conceptual design process. Results are presented for an optimized configuration along with several design trade cases. |
| NASA分類 | LAUNCH VEHICLES AND SPACE VEHICLES |
| レポートNO | 94A10718
AIAA PAPER 93-3967 |
| 権利 | Copyright |
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