A COMPREHENSIVE STUDY OF SHOCK BOUNDARY LAYER INTERACTION AND VARIOUS TECHNIQUES

Authors

  • Samadarshi Adhikari Department of Aerospace Engineering, Amity University Haryana, Gurugram, India
  • Sonia Chalia Department of Aerospace Engineering, Amity University Haryana, Gurugram, India

Keywords:

Shock Wave, Boundary Layer, Particle Image Velocimetry, Micro Vortex Generator, High Supersonic Tunnel, Schlieren Photography

Abstract

Shock boundary layer interaction is an undesirable event occurring in high speed aircrafts causes boundary
layer separation which leads to pressure drop, undesirable heating load, vibrations, drop in aircraft performance and
controlling ability. To remove these undesirable events the flow field is analyzed and diagnosed by micro vortex
generators on aircraft body using flow visualization tools. Experimental techniques such as High speed Wind tunnels,
Particle Image Velocimetry, Schlieren photography, oil-flow visualization are studied to analysis the changes in flow
properties when shock interacts with boundary layer.

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Published

2018-04-25

How to Cite

Samadarshi Adhikari, & Sonia Chalia. (2018). A COMPREHENSIVE STUDY OF SHOCK BOUNDARY LAYER INTERACTION AND VARIOUS TECHNIQUES. International Journal of Advance Engineering and Research Development (IJAERD), 5(4), 2168–2173. Retrieved from https://www.ijaerd.org/index.php/IJAERD/article/view/5560

Issue

Vol. 5 No. 4 (2018): Volume 5 Issue 4 April 2018

Section

Articles