Triangular Wings Cambered and Twisted to Support Specified Distributions of Lift at Supersonic Speeds

摘要

The linearized supersonic flow theory has been applied 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 have been derived and plots of the cambered surfaces, the corresponding lift distributions, and values of the theoretical drag coefficients are presented. The examples were chosen to avoid the singularities in lift distribution or camber that appear in previously given solutions and may be useful for practical applications since they avoid large pressure peaks and extreme angles of twist.