Effect of Unit Reynolds Number, Nose Bluntness, Angle of Attack, and Roughness on Transition on a 5 Deg Half-Angle Cone at Mach 8
1969
78 pages
Report
Keine Angabe
Englisch
Aerodynamics , Angle of attack , Blunt bodies , Circular cones , Hypersonic flow , Mach number , Reynolds number , Surface roughness effects , Blowdown wind tunnels , Boundary layer transition , Free flow , Laminar boundary layer , Stanton number , Turbulent boundary layer , Turbulent heat transfer , Wall temperature , Wind tunnel models