LAWS-Lift analysis of wings in supersonic flows

A computer program 'called LAWS has been developed for the Lift Analysis of Wings In Supersonic flows. The program Is based on supersonic linearized theory integral equations and the Mach box method of wing representation Given the planform and the free stream Mach number, the code computes the lifting pressure distribution over the wing . surface and the associated force coefficients. The methodology used here is valid for flat wings with any complex planform. Comparison of the results for flat delta and arrow wings show good agreement with the -exact solutions . The Input and output information for program LAWS is . available in the help file of code NALSOF0507 of the SOFFTS library at NAL