| タイトル | Effects of Cone Angle, Mach Number, and Nose Blunting on Transition at Supersonic Speeds |
| 本文（外部サイト） | http://hdl.handle.net/2060/20040006462 |
| 著者（英） | Jackson, Mary W.; Czarnecki, K. R. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1961-01-01 |
| 言語 | eng |
| 内容記述 | An investigation has been made to determine the transition characteristics of a group of blunt cones which varied in included apex angle from 27 deg to 60 deg over a Mach number range from 1.61 to 2.20 and a range of tunnel Reynolds number per foot from about 1.5 x 10(exp 6) to 8.0 x 10(exp 6). The tests were made at zero angle of attack and with zero heat transfer. The results indicate that the general level of transition Reynolds number based on boundary-layer momentum thickness and local flow conditions just outside the boundary layer varied between 600 and 1,100. Changes in Mach number had little effect on transition distance and transition Reynolds number for the near-sharp or very small bluntnesses. The effect of Mach number variation on the larger hemispherical bluntnesses was much stronger, with the strongest Mach number effect occurring for Mach numbers between 1.61 and 1.82. With an increase in nose radius, there was a strong decrease in transition distance and transition Reynolds number at the lower Mach numbers. This adverse effect tended to become weaker with increase in Mach number. An increase in cone angle at a constant Mach number caused a reduction in transition distance and transition Reynolds number for the blunt configurations which had approximately the same values of nose radius. |
| NASA分類 | Aerodynamics |
| レポートNO | NASA-TN-D-634 |
| 権利 | No Copyright |
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