| タイトル | Plans for in-flight measurement of hypersonic crossflow transition on the Pegasus launch vehicle |
| 著者（英） | Godil, Afzal; Noffz, Greg K.; Bertelrud, Arild; Kolodziej, Paul |
| 著者所属（英） | NASA Langley Research Center; NASA Hugh L. Dryden Flight Research Facility; NASA Ames Research Center |
| 発行日 | 1992-08-01 |
| 言語 | eng |
| 内容記述 | A flight measurements program is underway to obtain flight data for validating stability theory-based transition estimation techniques for crossflow-induced boundary-layer transition at Mach 6-8. A smooth wing glove, designed to enhance crossflow transition and suppress Tollmien-Schlichting (T-S) instabilities, will be mounted on the delta wing of the first stage of the Pegasus booster. The instrumentation package will include 'intelligent' software capable of yielding space and time-correlations obtained through extensive use of fast Fourier transforms (FFTs), 'windowing' and multistage compression as well as a variety of techniques for quality assurance. The flight experiment covers a Mach number range (6 to 8) where low background disturbance data cannot currently be obtained in ground facilities. These flight results will support transition estimation code development for application to supersonic laminar flow control (LFC) and National Aero-Space Plane (NASP) class vehicles in areas where crossflow, rather than T-S waves, is the dominant instability mode. |
| NASA分類 | AIRCRAFT INSTRUMENTATION |
| レポートNO | 93A13260
AIAA PAPER 92-4104 |
| 権利 | Copyright |
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