| タイトル | Numerical simulation of the Space Shuttle Launch Vehicle flowfield with real gas solid rocket plume effects |
| 著者（英） | Martin, F. W., Jr.; Kandula, M.; Slotnick, J. P.; Buning, P. G. |
| 著者所属（英） | NASA Ames Research Center; NASA Johnson Space Center |
| 発行日 | 1993-01-01 |
| 言語 | eng |
| 内容記述 | A numerical simulation of the external ascent flowfield of the Space Shuttle Launch Vehicle (SSLV) was carried out at the freestream Mach number 1.25, the angle of attack -5.1 deg, and the flight Reynolds number 3.25 x 10 exp 6/ft. The simulation is an extension of the solution by Kandula et al. (1991) and incorporates variable gamma effects with a high fidelity grid appropriate for a flight Reynolds number flow solution. Three-dimensional SSLV steady-state simulations with either perfect-gas or variable-gamma-gas Redesigned-Solid-Rocket-Motor (RSRM) plumes are computed on a 14-grid overlapping body-conforming grid system, and the influence of the RSRM exhaust plumes on the SSLV component pressure distributions and integrated loads is examined. |
| NASA分類 | SPACECRAFT PROPULSION AND POWER |
| レポートNO | 93A23263
AIAA PAPER 93-0521 |
| 権利 | Copyright |
|
