| タイトル | Pressure distributions on a flat-plate delta wing swept 65 deg at a Mach number of 5.97 at angles of attack from 65 deg to 115 deg and angles of roll from 0 deg to 25 deg at a 90 deg angle of attack |
| 本文（外部サイト） | http://hdl.handle.net/2060/19660024037 |
| 著者（英） | Goldberg, T. J.; Hondros, J. G. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1962-08-01 |
| 言語 | eng |
| 内容記述 | Pressure distributions on flat plate delta wing swept 65 deg at hypersonic speeds at angles of attack from 65 deg to 115 deg and angles of roll from 0 deg to 25 deg at 90 deg angle of attack |
| NASA分類 | AERODYNAMICS |
| レポートNO | 66N33327
NASA-TM-X-702 |
| 権利 | No Copyright |
