Unsteadiness of the shock wave structure in attached and separated compression ramp flows |
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| Authors: | D. S. Dolling C. T. Or |
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| Affiliation: | (1) Department of Aerospace Engineering and Engineering Mechanics, University of Texas at Austin, 78712-1085 Austin, Tex., USA;(2) Mechanical and Aerospace Engineering Department, Princeton University, New Jersey, USA |
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| Abstract: | Wall pressure fluctuations have been measured upstream of the corner-line in several two dimensional, adiabatic, compression ramp flows. The nominal freestream Mach number was 3 and the Reynolds number, based on boundary layer thickness, was 1.4 million. The measurements show that the shockwave structure is unsteady in both separated and attached flows, resulting in a region in which the wall pressure signal is intermittent. Statistical properties of this intermittent region, and of the separated flow, are presented and correlated with results from other studies. |
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