| タイトル | Flow fields and aerodynamic characteristics for hypersonic missiles with mid-fuselage inlets |
| 著者（英） | Riebe, G. D.; Hunt, J. L.; Johnston, P. J. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1983-01-01 |
| 言語 | eng |
| 内容記述 | A study was made to quantify forebody flow fields and to evaluate aerodynamic performance trends on a matrix of fuselage shapes for the mid-inlet/bolt-on-engine class of hypersonic airbreathing missiles for the Navy's vertical box launcher. The study indicated that inlet mass flow and pressure recovery can be increased by cambering the nose and increasing the width of the fuselage at both Mach 4 acceleration and Mach 6 cruise conditions. Aerodynamic trim predictions show that the drag at zero lift at Mach 4 decreases while the L/D max at Mach 6 increases with the nose camber, although these tendencies reverse with increasing width of maximum fuselage cross section. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 83A16777
AIAA PAPER 83-0542 |
| 権利 | Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/406124 |
