Boundary-layer Transition at Mach 3.12 as Affected by Cooling and Nose Blunting
Auteur : N. S. Diaconis, John R. Jack, Richard J. Wisniewski
Date de publication : 1957
Éditeur : National Advisory Committee for Aeronautics
Nombre de pages : 17
Résumé du livre
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 8,000,000.