| タイトル | Analysis of entry aerodynamic heat-transfer data for the orbiter wing lower surface |
| 著者（英） | Hartung, L. C.; Throckmorton, D. A. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1984-01-01 |
| 言語 | eng |
| 内容記述 | Flight-derived aerodynamic heat-transfer data for the orbiter wing lower surface, from STS-2, -3, and -5, are presented and compared with both ground-based experimental results and state-of-the-art computational flowfield results for a nominal angle of attack of 40 degrees. The flight data clearly show the development of the interference heat-transfer region on the wing lower surface resulting from the downstream effects of the bow-shock/wing-shock interaction. The location of the interference heating region is well correlated with a region of minimum static enthalpy near the boundary-layer edge as predicted by a 3-dimensional, inviscid flowfield computation. The magnitude of the interference heat transfer is no greater than the undisturbed laminar heat transfer which occurs during the 'peak aerodynamic heating' portion of entry. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 84A17958
AIAA PAPER 84-0227 |
| 権利 | Copyright |
|
