Title of article
Visualization of Shock Wave Phenomenon around a Sharp Cone Model at Hypersonic Mach Number in a Shock Tunnel using High Speed Schlieren Facility
Author/Authors
Saiprakash, M Department of Aerospace Engineering MIT Campus - Anna University, Chennai, India , SenthilKumar, C Department of Aerospace Engineering MIT Campus - Anna University, Chennai, India , Sunil, G. K Defence Research & Development Laboratory, Hyderabad, India , Rampratap, S. P Defence Research & Development Laboratory, Hyderabad, India , Shanmugam, V Defence Research & Development Laboratory, Hyderabad, India , Balu, G Defence Research & Development Laboratory, Hyderabad, India
Pages
8
From page
461
To page
468
Abstract
The flow field around a Sharp cone model configuration has been investigated by means of Schlieren facility in hypersonic shock tunnel. The time dependent evolution of flow around a cone of angle 11.38° with base radius of 150mm has been visualized for a flow Mach number M = 6.5. Experiments have been carried out with Helium as driver gas and air as test gas to visualize the hypersonic flow field. The flow establishment, steady state, and termination process of the hypersonic flow have been visualized for two different angles of attack, namely 0°&5°. Experimentally measured shock angle compares well with the theoretical and the computational study. The measured shock layer thickness compares well with the numerical simulation for both angles of attack.
Keywords
Shock layer thickness , Tunnel , Hypersonic shock , High speed Schlieren facility , Sharp Cone model
Journal title
Astroparticle Physics
Serial Year
2019
Record number
2467355
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