| タイトル | Experimental investigation to validate use of cryogenic temperatures to achieve high Reynolds numbers in boattail pressure testing |
| 本文（外部サイト） | http://hdl.handle.net/2060/19760023140 |
| 著者（英） | Reubush, D. E. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1976-08-01 |
| 言語 | eng |
| 内容記述 | An investigation has been conducted in the Langley 1/3 meter transonic cryogenic tunnel to validate the use of cryogenic temperatures to achieve high Reynolds numbers in nozzle boattail pressure testing. Tests were conducted at 0 degree angle of attack and at Mach numbers of 0.60, 0.85, and 0.90 on two wing-body configurations with differing boattail geometries. Test data were obtained by using two different techniques, the cryogenic method and the conventional method, to obtain the same Reynolds number. Later, the test data obtained from the two techniques on boattail pressure coefficient distributions and pressure drag coefficients were compared; results from the comparisons show excellent repeatability for all test conditions and indicate no measurable errors when using cryogenic temperatures to achieve high Reynolds numbers for nozzle boattail pressure testing. |
| NASA分類 | RESEARCH AND SUPPORT FACILITIES (AIR) |
| レポートNO | 76N30228
L-10827
NASA-TM-X-3396 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/184824 |
