| タイトル | Hyper-X Mach 7 Scramjet Design, Ground Test and Flight Results |
| 本文（外部サイト） | http://hdl.handle.net/2060/20050215122 |
| 著者（英） | Ferlemann, Shelly M.; Rock, Ken E.; McClinton, Charles R.; Voland, Randy T. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 2005-01-01 |
| 言語 | eng |
| 内容記述 | The successful Mach 7 flight test of the Hyper-X (X-43) research vehicle has provided the major, essential demonstration of the capability of the airframe integrated scramjet engine. This flight was a crucial first step toward realizing the potential for airbreathing hypersonic propulsion for application to space launch vehicles. However, it is not sufficient to have just achieved a successful flight. The more useful knowledge gained from the flight is how well the prediction methods matched the actual test results in order to have confidence that these methods can be applied to the design of other scramjet engines and powered vehicles. The propulsion predictions for the Mach 7 flight test were calculated using the computer code, SRGULL, with input from computational fluid dynamics (CFD) and wind tunnel tests. This paper will discuss the evolution of the Mach 7 Hyper-X engine, ground wind tunnel experiments, propulsion prediction methodology, flight results and validation of design methods. |
| NASA分類 | Fluid Mechanics and Thermodynamics |
| 権利 | No Copyright |
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