| タイトル | Hypervelocity Capability of the HYPULSE Shock-Expansion Tunnel for Scramjet Testing |
| 本文（外部サイト） | http://hdl.handle.net/2060/20010059583 |
| 著者（英） | Tsai, Ching-Yi; Shih, Ann T.; Bakos, Robert J.; Rogers, R. Clayton; Foelsche, Robert O. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 2001-01-01 |
| 言語 | eng |
| 内容記述 | New hypervelocity capabilities for scramjet testing have recently been demonstrated in the HYPULSE Shock-Expansion Tunnel (SET). With NASA's continuing interests in scramjet testing at hypervelocity conditions (Mach 12 and above), a SET nozzle was designed and added to the HYPULSE facility. Results of tests conducted to establish SET operational conditions and facility nozzle calibration are presented and discussed for a Mach 15 (M15) flight enthalpy. The measurements and detailed computational fluid dynamics calculations (CFD) show the nozzle delivers a test gas with sufficiently wide core size to be suitable for free-jet testing of scramjet engine models of similar scale as, those tested in conventional low Mach number blow-down test facilities. |
| NASA分類 | Research and Support Facilities (Air) |
| レポートNO | ISSW23 Paper-1047 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/92890 |
