Saravanan, S and Nagashetty, K and Hegde, GM and Jagadeesh, G and Reddy, KPJ (2011) Schlieren visualization of shock wave phenomena over a missile-shaped body at hypersonic Mach numbers. In: Proceedings of the Institution of Mechanical Engineers - Part G: Journal of Aerospace Engineering, 225 (G1). pp. 26-34.
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The flow over a missile-shaped configuration is investigated by means of Schlieren visualization in short-duration facility producing free stream Mach numbers of 5.75 and 8. This visualization technique is demonstrated with a 41 degrees full apex angle blunt cone missile-shaped body mounted with and without cavity. Experiments are carried out with air as the test gas to visualize the flow field. The experimental results show a strong intensity variation in the deflection of light in a flow field, due to the flow compressibility. Shock stand-off distance measured with the Schlieren method is in good agreement with theory and computational fluid dynamic study for both the configurations. Magnitude of the shock oscillation for a cavity model may be greater than the case of a model without cavity. The picture of visualization shows that there is an outgoing and incoming flow closer to the cavity. Cavity flow oscillation was found to subside to steady flow with a decrease in the free stream Mach number.
|Item Type:||Journal Article|
|Additional Information:||Copyright of this article belongs to Professional Engineering Publishing.|
|Keywords:||flow visualization; missile-shaped body; stagnation enthalpy; forward-facing cavity; Schlieren method; shock stand-off distance|
|Department/Centre:||Division of Mechanical Sciences > Aerospace Engineering (Formerly, Aeronautical Engineering)|
|Date Deposited:||03 Mar 2011 12:26|
|Last Modified:||03 Mar 2011 12:26|
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