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

N. S. Diaconis, John R. Jack, Richard J. Wisniewski
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.

An Adobe Acrobat (PDF) file of the entire report: