| タイトル | Calibration of propulsion simulation nozzles for space shuttle booster and orbiter models for the abort/separation staging experimental program |
| 本文（外部サイト） | http://hdl.handle.net/2060/19730014087 |
| 著者（英） | Baker, L. R., Jr. |
| 著者所属（英） | Lockheed Missiles and Space Co. |
| 発行日 | 1971-07-01 |
| 言語 | eng |
| 内容記述 | An experimental program to determine the power-on aerodynamic flight characteristics of the booster and orbiter vehicles during the abort separation maneuver is reported. An essential contribution to such a test program is the gas dynamic simulation of the size and shape of the plumes emitting from the full-scale orbiter and booster main propulsion systems. The two major effects of the plume which must be simulated are: the interaction of the plume with the external flow field, and the direct impingement of the plumes on surfaces which are enveloped by the plume. To accomplish the objective of correct plume simulation, the similarity parameters developed by Herron and the requirement to match momentum flux per unit area between the model and the full-scale systems, were applied to the orbiter and booster propulsion systems. |
| NASA分類 | SPACE VEHICLES |
| レポートNO | 73N22814
LMSC/HREC-D225144
NASA-CR-124217
TM-54/20-320 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/199353 |
