原文传递
Test Capabilities and Recent Experiences in the NASA Langley 8-Foot High Temperature Tunnel
| 题名： | Test Capabilities and Recent Experiences in the NASA Langley 8-Foot High Temperature Tunnel |
| 作者： | Hodge, Jeffrey S.; Harvin, Stephen F. |
| 关键词： | capabilities；temperature；tunnel；langley；nasa；combustion；nces；high；ence；breath |
| 摘要： | The NASA Langley 8-Foot High Temperature Tunnel is a combustion-heated hypersonic blowdown-to-atmosphere wind tunnel that provides flight enthalpy simulation for Mach numbers of 4, 5, and 7 through an altitude range from 50,000 to 120,000 feet. The open-.jet test section is 8-ft. in diameter and 12-ft. long. The test section will accommodate large air-breathing hypersonic propulsion systems as well as structural and thermal protection system components. Stable wind tunnel test conditions can be provided for 60 seconds. Additional test capabilities are provided by a radiant heater system used to simulate ascent or entry heating profiles. The test medium is the combustion products of air and methane that are burned in a pressurized combustion chamber. Oxygen is added to the test medium for air-breathing propulsion tests so that the test gas contains 21 percent molar oxygen. The facility was modified extensively in the late 1980's to provide airbreathing propulsion testing capability. In this paper, a brief history and general description of the facility are presented along with a discussion of the types of supported testing. Recently completed tests are discussed to explain the capabilities this facility provides and to demonstrate the experience of the staff. |
| 报告类型： | 科技报告 |
相关文献
- CFD Model Of The Transonic Dynamics Tunnel With Applications [STUB].
- Characterization of the Test Section Walls at the 14- by 22-Foot Subsonic Tunnel
- A Description of the and quotCrow's Foot and quot Tunnel Concept
- Wind Tunnel Measured Effects on a Twin-Engine Short-Haul Transport Caused by Simulated Ice Accretions Data Report
- Background Pressure Profiles for Sonic Boom Vehicle Testing in the NASA Glenn 8- by 6-Foot Supersonic Wind Tunnel.
- Wind Tunnel Measured Effects on a Twin-Engine Short-Haul Transport Caused by Simulated Ice Accretions
检索历史
应用推荐
