Instability and transition in supersonic boundary layers

摘要: Recently obtained flight transition data for a 5-deg half-angle cone at Mach numbers of 1.2, 1.35, 1.6, and 1.92, together with 'quiet' tunnel 3.5, are analyzed by linear compressible stability theory. The results indicate that the exponent N ranges in value between 9 11, which is keeping values previously determined subsonic flows. Computations show both quiet wind experiments was due to oblique first-mode disturbances.