The analysis indicates that for aerodynamic efficiency, wings designed for flight at supersonic speeds should be swept back at an angle greater than the Mach angle and the angle of sweepback should be such that the component of velocity normal to the leading edge is less than the critical speed of the airfoil sections. This principle may also be applied to wings designed for subsonic speeds near the speed of sound, for which the induced velocities resulting from the thickness might otherwise be sufficiently great to cause shock waves.
Wing planforms for high-speed flight
1976-02-01
Miscellaneous
No indication
English
Aerodynamic Properties of Crescent Wing Planforms
Online Contents | 1994
|Wing planforms for large military transports
AIAA | 1978
|