Venukumar, Balla and Reddy, KPJ (2007) Experimental investigation of drag reduction by forward facing high speed gas jet for a large angle blunt cone at Mach 8. In: Sadhana: Academy Proceedings in Engineering Sciences, 32 (1-2). pp. 123-131.
Substantial aerodynamic drag, while flying at hypersonic Machnumber, due to the presence of strong standing shock wave ahead of a large-angle bluntcone configuration, is a matter of great design concern. Preliminary experimental results for the drag reduction by a forward-facing supersonic air jet for a 60◦ apexangle blunt cone at a flow Mach number of 8 are presented in this paper. The measurements are carried out using an accelerometer-based balance system in the hypersonic shock tunnel HST2 of the Indian Institute of Science, Bangalore. About 29% reduction in the drag coefficient has been observed with the injection of a supersonic gas jet.
|Item Type:||Journal Article|
|Additional Information:||Copyright of this article belongs to Indian Academy of Sciences.|
|Keywords:||Aerodynamic drag;Hypersonic flow;Shock tunnel;Air jet;Force balance;Shock interaction|
|Department/Centre:||Division of Mechanical Sciences > Aerospace Engineering (Formerly, Aeronautical Engineering)|
|Date Deposited:||06 Sep 2007|
|Last Modified:||19 Sep 2010 04:39|
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