Boundary-layer transition at Mach 3.12 as affected by cooling and nose blunting

N. S. Diaconis, John R. Jack, Richard J. Wisniewski
naca-tn-3928
Jan 1957


An investigation was made to determine the combined effects of nose blunting and cooling on boundary-layer transition. Data are presented for both sharp and blunted cone-cylinder and parabolic -nosed-cylinder bodies at Reynolds numbers per foot up to 8 X 10 to the sixth.

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