Boundary-Layer Stability Analysis on a Parametric Hypersonic Finned Circular Cone
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© 2019, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. This paper provides a combined experimental and computational analysis of a hypersonic finned cone geometry. Experimental results from the Boeing/AFOSR Mach-6 Quiet Tunnel analyzing the heating on a portion of the surface of the cone are presented. They are compared to computational heating computed in the same manner in the same region. It is found that experiments and computations agree well quantitatively at lower unit Reynolds numbers whereas they begin to differ at higher unit Reynolds numbers due to the experiments measuring flow that is at least transitional. In addition, experimental pressure fluctuation measurements taken on the cone surface as well as the side of the fin using pressure sensors are detailed. Computationally, the linear parabolized stability equations are used to probe the flow for instabilities that are present both on the surface of the cone and on the side of the fin in the vicinity of these sensors. By analyzing both experimental results and LPSE computations, the second mode instability mechanism is found to be present on this geometry, both on the cone and fin. Further investigation is ongoing using instability methods such as spatial BiGlobal which are needed to examine regions of the flow with large spanwise variance, such as in the vicinity of horseshoe vortex or in the corner of the fin and cone.
author list (cited authors)
Mullen, C. D., Turbeville, F. D., Reed, H. L., & Schneider, S. P.