The results of Murman and Krupp (1971) are used to develop a procedure for computing a transonic flow about a finite lifting wing. A small disturbance equation describing the velocity potential of three-dimensional wings is solved in the process. The procedure is applied to a wing with a symmetric biconvex airfoil section in a zero-incidence subsonic flow, to a supersonic rectangular lifting wing with a sharp leading edge and to a subcritical nonlifting rectangular wing with a blunt leading edge.
Computation of transonic flow about finite lifting wings.
AIAA Journal ; 10
1972-07-01
Miscellaneous
No indication
English
Computation of Transonic Flow about Finite Lifting Wings
AIAA | 1972
|Transonic flow past lifting wings.
NTRS | 1973
|Transonic flow past lifting wings.
AIAA | 1973
|