Under the auspices of NATO STO AVT-240: “Hypersonic Boundary-Layer Transition Prediction”, this paper describes the results of close collaborations among the authors toward the fundamental understanding and modeling of the instabilities associated with three-dimensional boundary layers in hypersonic flight. Specifically, the focus is directed toward the crossflow instability. A common straight circular cone geometry is analyzed for M = 5.91 6 and R e = 9.8 10.1 × 10 6 / m from both a computational and experimental perspective using methods that are unique to each facility and methodology. Disturbance wavelength and trajectory, surface roughness, and the use of quiet wind tunnels are just a few items found to be key factors in the investigation of the crossflow instability. Quiet tunnels allow experiments to be performed in a disturbance environment comparable to that expected from flight, and the combination of different facilities and computations displays a comprehensive analysis that would be unobtainable from any individual approach alone.


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    Title :

    Hypersonic Crossflow Instability



    Published in:

    Publication date :

    2018-10-26


    Size :

    15 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




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