Saravanan, S and Nagashetty, K and Jagadeesh, G and Reddy, KPJ (2009) Experimental investigation of heat transfer reduction using forward facing cavity for missile shaped bodies flying at hypersonic speed. In: 26th International Symposium on Shock Waves, JUL 15-20, 2007, Gottingen, Germany, pp. 613-617.Full text not available from this repository. (Request a copy)
Forward facing circular nose cavity of 6 mm diameter in the nose portion of a generic missile shaped bodies is proposed to reduce the stagnation zone heat transfer. About 25% reduction in stagnation zone heat transfer is measured using platinum thin film sensors at Mach 8 in the IISc hypersonic shock tunnel. The presence of nose cavity does not alter the fundamental aerodynamic coefficients of the slender body. The experimental results along with the numerically predicted results is also discussed in this paper.
|Item Type:||Conference Paper|
|Additional Information:||Copyright of this article belongs to Springer|
|Department/Centre:||Division of Mechanical Sciences > Aerospace Engineering (Formerly, Aeronautical Engineering)|
|Date Deposited:||13 Dec 2009 10:44|
|Last Modified:||13 Dec 2009 10:44|
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