An experimental investigation was performed at Mach 10.4 in air on a 30 inch flat plate model with cylindrical leading edges of 0.002 inches, 0.063 inches, and 0.50 inches in diameter to examine the leading edge thickness effection the laminar boundary layer. The free stream Reynolds number based on leading edge diameter was varied between 73 and 70,000. Wall pressure distributions, boundary layer impact pressure surveys, and wall heat transfer distributions were measured and velocity profiles, boundary layer growth, skin friction, and Reynolds analogy factor were determined.
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