Chamkha, AJ and Takhar, HS and Nath, G (2005) Unsteady compressible boundary layer flow over a circular cone near aplane of symmetry. In: Heat and Mass Transfer, 41 (7). pp. 632641.

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Abstract
An analysis has been performed to study the unsteady laminar compressible boundary layer governing the hypersonic flow over a circular cone at an angle of attack near a plane of symmetry with either in flow or out flow in the presence of suction. The flow is assumed to be steady at time t= 0 and at t > 0 it becomes unsteady due to the timedependent free stream velocity which varies arbitrarily with time. The nonlinear coupled parabolic partial differential equations under boundary layer approximations have been solved by using an implicit finitedifference method. It is found that suction plays an important role in stabilising the fluid motion and in obtaining unique solution of the problem. The effect of the cross flow parameter is found to be more pronounced on the cross flow surface shear stress than on the streamwise surface shear stress and surface heat transfer.Beyond a certain value of the cross flow parameter overshoot in the cross flow velocity occurs and the magnitude of this overshoot increases with the cross flow parameter. The time variation of the streamwise surface shear stress is more significant than that of the cross flow surface shear stress and surface heat transfer. The suction and the total enthalpy at the wall exert strong infuence on the streamwise and cross flow surface shear stresses and the surface heat transfer except that the effect of suction on the cross flow surfaces hear stress is small.
Item Type:  Journal Article 

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Additional Information:  Copyright for this article belongs to Springer. 
Department/Centre:  Division of Physical & Mathematical Sciences > Mathematics 
Date Deposited:  08 Jun 2005 
Last Modified:  19 Sep 2010 04:19 
URI:  http://eprints.iisc.ernet.in/id/eprint/3292 
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