The flow physics associated with shock-wave/boundary-layer interactions (SBLIs) on an axisymmetric body, simulating a projectile near an aircraft, is of significant interest to the aerodynamic community. The main objective of this experimental study is to investigate SBLIs on an axisymmetric configuration involving curved surfaces as compared to two-dimensional and three-dimensional (3-D) canonical configurations with flat surfaces. The experiments were carried out at Mach 2, and the planar shock wave was generated using a wedge-shaped shock generator with a turn angle of 10 deg. Measurements include steady and unsteady pressures, surface oil flow, and shadowgraph flow visualizations on the axisymmetric body. Results of the surface flow visualizations and steady pressure contours show that the separation on the body is an open-type region similar to that observed for 3-D SBLI canonical configurations. Flow separation on the surface is driven by pressure gradients caused by both the impingement of the oblique shock and the curvature of the body. Unsteady pressure measurements reveal that the shock impingement on the surface is governed by large-amplitude pressure fluctuations beneath the shock foot and flow reattachment regions.


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    Title :

    Shock-Wave/Boundary-Layer Interactions on an Axisymmetric Body at Mach 2


    Contributors:

    Published in:

    AIAA Journal ; 59 , 11 ; 4530-4543


    Publication date :

    2021-11-01




    Type of media :

    Conference paper , Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English





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