| タイトル | PNS predictions for supersonic/hypersonic flows over finned missile configurations |
| 著者（英） | Bhutta, Bilal A.; Lewis, Clark H. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1992-06-01 |
| 言語 | eng |
| 内容記述 | Finned missile design entails accurate and computationally fast numerical techniques for predicting viscous flows over complex lifting configurations at small to moderate angles of attack and over Mach 3 to 15; these flows are often characterized by strong embedded shocks, so that numerical algorithms are also required to capture embedded shocks. The recent real-gas Flux Vector Splitting technique is here extended to investigate the Mach 3 flow over a typical finned missile configuration with/without side fin deflections. Elliptic grid-generation techniques for Mach 15 flows are shown to be inadequate for Mach 3 flows over finned configurations and need to be modified. Fin-deflection studies indicate that even small amounts of missile fin deflection can substantially modify vehicle aerodynamics. This 3D parabolized Navier-Stokes scheme is also extended into an efficient embedded algorithm for studying small axially separated flow regions due to strong fin and control surface deflections. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 93A37374
AIAA PAPER 92-2695 |
| 権利 | Copyright |
