Sahoo, Niranjan and Kulkarni, Vinayak and Saravanan, S and Jagadeesh, G and Reddy, KPJ (2005) Film cooling effectiveness on a large angle blunt cone flying at hypersonic speed. In: Physics of Fluids, 17 . 036102 :1-11.
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Effectiveness of film cooling technique to reduce convective heating rates for a large angle blunt cone flying at hypersonic Mach number and its effect on the aerodynamic characteristics is investigated experimentally by measuring surface heat-transfer rates and aerodynamic drag coefficient simultaneously. The test model is a 60° apex-angle blunt cone with an internally mounted accelerometer balance system for measuring aerodynamic drag and an array of surface mounted platinum thin film gauges for measuring heat-transfer rates. The coolant gas (air, carbon dioxide, and/or helium) is injected into the hypersonic flow at the nose of the test model. The experiments are performed at a flow free stream Mach number of 5.75 and 0° angle of attack for stagnation enthalpies of 1.16 MJ/kg and 1.6 MJ/kg with and without gas injection. About 30%–45% overall reduction in heat-transfer rates is observed with helium as coolant gas except at stagnation regions. With all other coolants, the reduction in surface heat-transfer rate is between 10%–25%. The aerodynamic drag coefficient is found to increase by 12% with helium injection whereas with other gases this increase is about 27%.
|Item Type:||Journal Article|
|Additional Information:||Copyright of this article belongs to the American Institute of Physics.|
|Department/Centre:||Division of Mechanical Sciences > Aerospace Engineering (Formerly, Aeronautical Engineering)|
|Date Deposited:||25 Aug 2008|
|Last Modified:||19 Sep 2010 04:36|
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