FREE FLIGHT EXPERIMENTAL INVESTIGATIONS OF THE EFFECT OF BOUNDARY LAYER COOLING ON TRANSITION
NAVAL ORDNANCE LAB WHITE OAK MD
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Free flight tests were conducted in the NOL Pressurized Ballistics Range for the purpose of investigating boundary layer transition under the conditions of extreme boundary layer cooling. The tests were conducted on smooth, sharp-nosed, slender cones. The tests were conducted at a nominal Mach number of 3 and a free stream unit Reynolds number per foot of 11.8 x 10 to the 6th power. The ratio of wall to adiabatic recovery temperature varied between 0.22 and 0.27. The results agreed very closely with results from wind tunnel test conducted at similar conditions. These free flight tests seem to substantiate earlier results which indicate a destabilizing trend for laminar boundary layers subjected to extreme cooling.