Stability of Hypersonic Compression Cones
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Our activities focus on the identification and understanding of the second-mode instability for representative configurations in hypersonic flight. These include the Langley 93-10 flared cone and the Purdue compression cone, both at 0° angle of attack at Mach 6. A nonlinear parabolized stability equation (NPSE) capability, called JoKHeR (Kuehl et al. 2012), is applied. Steady basic-state calculations are obtained with Pointwise and GASP. Verification studies are provided. Then, second-mode instabilities are modeled on the Langley 93-10 flared-cone model, and progress in validation with the experimental findings of Hofferth et al. (2012) is discussed. Through application of NPSE and linear parabolized stability equations (PSE) to both geometries, it is concluded that mean-flow distortion tends to amplify frequencies less than the peak frequency and stabilize those greater by modifying the boundary-layer thickness. As initial disturbance amplitude is increased and/or a broad spectrum disturbance is introduced, direct numerical simulations (DNS) or NPSE appear to be the proper choices to model the evolution, and relative evolution, because these computational tools include these nonlinear effects (mean-flow distortion). © 2012 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
author list (cited authors)
Perez, E., Kocian, T., Kuehl, J., & Reed, H.