Analysis of wings with leading edge and/or trailing edge segmented (spanwise) flaps using planar horse shoe vortex lattice method

A method and a computer program in FORTRAN have been developed for the analysis of wings with segmented leading edge and trailing edge flaps using planar horse-shoe vortices. This computer program can be used to estimate overall aerodynamic characteristics like C sub L, C sub D and C sub M and the detailed local loads for a given wing flap geometry at specified incidence and Mach number. The method has no limitations on aspect ratio, taper ratio and (Author)sweep angles. The code has been validated for a number of cases for which experimental data is available. The program is working on UNIVAC 1100-60 computer and takes about 2 minutes to analyze a typical wing-flap configuration (with approximately 120 panels) for a given incidence and Mach number