An Experimental Study Of Highly Cooled Boundary Layer Transition And Heat Transfer In Supersonic Flow

An Experimental Study of Highly Cooled Boundary Layer Transition and Heat Transfer in a Supersonic Flow

An experimental investigation of the effect of extreme wall cooling on boundary layer transition has been carried out on a 5.4 deg half-angle cone. The range of test conditions included unit Reynolds numbers from 1000 000 to 3500 000, local Mach numbers from 2.4 to 2.8, and wall-to-adiabatic wall enthalpy ratios from 0.018 to 0.045. Local transition Reynolds numbers were obtained from measurements of heat transfer distribution on the surface of the cone model and ranged from 550 000 to 1800 000, based on distance from the tip of the cone, over the range of conditions covered. The results indicate a decreasing transition Reynolds number with increasing wall cooling. A unit Reynolds number effect on transition was observed. (Author).

Research Review

Research Review