Hypersonic Wind-Tunnel Measurements of Boundary-Layer Pressure Fluctuations
PURDUE UNIV LAFAYETTE IN SCHOOL OF AERONAUTICS AND ASTRONAUTICS
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During atmospheric reentry, hypersonic vehicles are subjected to high levels of boundary-layer pressure fluctuations. To improve understanding and prediction of these fluctuations, measurements of surface pressure fluctuations on a seven-degree sharp cone at zero angle of attack were conducted in Sandias Hypersonic Wind Tunnel under noisy flow and in Purdue Universitys BoeingAFOSR Mach-6 Quiet Tunnel under noisy and quiet flow. Fluctuations under laminar boundary layers reflected tunnel noise levels. Laminar boundary-layer measurements under quiet flow were an order of magnitude lower than under noisy flow. Transition on the model only occurred under noisy flow, and fluctuations peaked during transition. The transition location, marked by the peak, depended on tunnel noise parameters.
- Research and Experimental Aircraft
- Test Facilities, Equipment and Methods
- Fluid Mechanics