Shock-boundary layer interaction (SBLI) at hypersonic inlets can alter the flow pattern and impose adverse effects on engine operation if not controlled. A two-dimensional surface modification in the form of a sinusoidal wavy patch was introduced to a standard wedge-plate model in a hypersonic freestream of Mach 8.5 to test its influence on incident SBLI. Experimental and numerical comparison of flow visualization and wall pressure readings on the model with and without the wavy patch indicated a mitigating effect of the wavy patch on incident SBLI. The controlled SBLI induced significantly smaller flow separation compared with an uncontrolled case. Because of the minimally intrusive design of the wavy patch, the flow distortion/instability was notably less than that observed in the uncontrolled case.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Hypersonic Incident Shock-Boundary Layer Interaction Control by Wavy Patches


    Contributors:

    Published in:

    Publication date :

    2020-09-24




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    Unknown




    Incident Shock Wave/Turbulent Boundary Layer Interaction in a Hypersonic Flow

    Chung, K.-M. / Lu, F. K. | British Library Conference Proceedings | 1993


    Hypersonic Boundary Layer Treatment With Wavy Wall

    Ruggeri, Matteo / Bemis, Benjamin L. / Sieve, Megan C. et al. | AIAA | 2024


    Hypersonic shock/boundary-layer interaction database

    SETTLES, G. / DODSON, L. | AIAA | 1991


    Stabilization of a Hypersonic Boundary Layer Using a Wavy Surface

    Bountin, D. / Chimitov, T. / Maslov, A. et al. | British Library Conference Proceedings | 2012