| タイトル | Mach 3.5 boundary-layer transition on a cone at angle of attack |
| 著者（英） | King, Rudolph A. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1991-06-01 |
| 言語 | eng |
| 内容記述 | Boundary-layer transition on a sharp 5-deg half-angle cone at incidence was investigated at Mach 3.5 in NASA's Supersonic Low-Disturbance Pilot Tunnel. The tests were conducted with low and high levels of freestream acoustic disturbance, and four angles of attack (alpha/theta-c = 0, 0.12, 0.4, and 0.8). Transition data, obtained with and without significantly reduced freestream acoustic disturbance levels, are compared with conventional ('noisy') wind-tunnel data. It was found that, under quiet flow conditions, there was no significant unit Reynolds number effect, whereas with noisy flow conditions, a significant unit Reynolds number effect was measured on and near the windward ray for alpha/theta-c values 0.4 and 0.8. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 91A43650
AIAA PAPER 91-1804 |
| 権利 | Copyright |
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