Experimental determination of boundary-layer transition on a body of revolution at M = 3.5

James R. Jedlicka, Max E. Wilkins, Alvin Seiff
naca-tn-3342
Oct 1954


Transition tests were made in free-flight on a slender body of revolution at a Mach number of 3.5, wall to free-stream temperature ratio of unity, and with a noiseless and zero-turbulence air stream. The parameter which was varied was surface roughness.

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