Hypersonic Boundary Layer Cross Flow Transition - Characteristics and Control
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© 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. The paper focuses on a topic area of the NATO AVT-240 Working Group on Hypersonic Boundary Layer Transition dealing with the 3-D boundary layer cross-flow instability that is expected to be dominant mechanism of turbulent transition on hypersonic lift-generating shapes. The model geometries of interest to the Working Group are a 7° half-angle right-circular cone at a 6° angle of attack, and a 2:1 elliptic cone at a 0° angle of attack. The focus is on the prediction and control of turbulent transition in these cases, as well as the sensitivity to initial conditions including surface roughness, and free-stream acoustic disturbance levels. Finally, potential interactions between stationary and the traveling cross-flow modes that might play a role in transition are highlighted. The cited results will primarily originate from experiments in three different Mach 6 facilities of different designs. This provides an opportunity to investigate the effect, if any, of different freestream characteristics on the cross-flow transition.
author list (cited authors)
Corke, T. C., & Bowersox, R. D.