Sreekanth , * and Reddy, NM (1995) Study of transpiration cooling over a flat plate at hypersonic Mach numbers. In: Journal of Thermophysics and Heat Transfer, 9 (3). pp. 552-555.Full text not available from this repository.
Transpiration cooling over a flat plate at hypersonic Mach numbers is analyzed using Navier-Stokes equations, without the assumption of an isothermal wall with a prescribed wall temperature. A new criterion is proposed for determining a relevant range of blowing rates, which is useful in the parametric analysis. The wall temperature is found to decrease with the increasing blowing rate, but this effect is not uniform along the plate. The effect is more pronounced away from the leading edge. The relative change in the wall temperature is affected stronger by blowing at high Reynolds numbers. (AIAA)
|Item Type:||Editorials/Short Communications|
|Additional Information:||Copyright of this article belongs to American Institute of Aeronautics and Astronautics.|
|Department/Centre:||Division of Mechanical Sciences > Aerospace Engineering (Formerly, Aeronautical Engineering)|
|Date Deposited:||26 May 2011 05:41|
|Last Modified:||26 May 2011 05:41|
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