Sahoo, Niranjan and Saravanan, S and Jagadeesh, G and Reddy, KPJ (2006) Simultaneous measurement of aerodynamic and heat transfer data for large angle blunt cones in hypersonic shock tunnel. In: Sadhana, 31 (Part 5). pp. 557-581.
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Aerodynamic forces and fore-body convective surface heat transfer rates over a 60 degrees apex-angle blunt cone have been simultaneously measured at a nominal Mach number of 5.75 in the hypersonic shock tunnel HST2. An aluminum model incorporating a three-component accelerometer-based balance system for measuring the aerodynamic forces and an array of platinum thin-film gauges deposited on thermally insulating backing material flush mounted on the model surface is used for convective surface heat transfer measurement in the investigations. The measured value of the drag coefficient varies by about +/-6% from the theoretically estimated value based on the modified Newtonian theory, while the axi-symmetric Navier-Stokes computations overpredict the drag coefficient by about 9%. The normalized values of measured heat transfer rates at 0 degrees angle of attack are about 11% higher than the theoretically estimated values. The aerodynamic and the heat transfer data presented here are very valuable for the validation of CFD codes used for the numerical computation of How fields around hypersonic vehicles.
|Item Type:||Journal Article|
|Additional Information:||Copyright of this article belongs to Springer.|
|Keywords:||Aerodynamic and heat transfer data - large angle blunt cone - hypersonic flow shock tunnel.|
|Department/Centre:||Division of Mechanical Sciences > Aerospace Engineering (Formerly, Aeronautical Engineering)
Division of Mechanical Sciences > Mechanical Engineering
|Date Deposited:||03 Aug 2010 10:25|
|Last Modified:||19 Sep 2010 06:12|
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