Triangular wings cambered and twisted to support specified distributions of lift at supersonic speeds
Description:
Report presenting an application of the linearized supersonic flow theory to the calculation of the camber and twist required for various lift distributions on a triangular wing with leading edges behind the Mach cone. Several specific examples are used and plots of the cambered surfaces, corresponding lift distributions, and values of the theoretical drag coefficients are presented.
Date:
February 1949
Creator:
Baldwin, Barrett S., Jr.
Partner:
UNT Libraries Government Documents Department