| タイトル | High Reynolds number test of a NACA 651-213, a equals 0.5 airfoil at transonic speeds |
| 本文（外部サイト） | http://hdl.handle.net/2060/19750013179 |
| 著者（英） | Blackwell, J. A., Jr.; Pounds, G. A.; Burdges, K. P. |
| 著者所属（英） | Lockheed Aircraft Corp. |
| 発行日 | 1975-03-01 |
| 言語 | eng |
| 内容記述 | Wind-Tunnel tests were conducted in the Lockheed-Georgia Company's compressible flow facility to determine the transonic two-dimensional aerodynamic characteristics of a NACA 65 sub 1-213 a = 0.50 airfoil. The results are correlated with data obtained in the NASA-Langley 8-foot transonic pressure tunnel and the NAE high Reynolds number 15x60-inch two-dimensional test facility. The tests were conducted over a Mach number range from 0.60 to 0.80 and an angle of attack range from -1 deg to 8 deg. Reynolds numbers, based on the airfoil chord, were varied. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 75N21251
NASA-CR-2499 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/190437 |
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