Steady state aerodynamic analysis of aeroplane wings with constant and varying cross section

This paper presents a FORTRAN program for estimating aerodynamic characteristics of a wing planform of constant and varying cross-section of an aeroplane using Vortex Lattice Method (VLM). The Aerodynamic characteristics of interest are Lift, Drag acting on different parts of the wing. The program was developed to understand the effect of various parameters such as Aspect Ratio (AR), Sweep Back angle, Vortex or Panel formation and ground proximity on Lift and Drag and also to decide the wing dimensions for different wing configurations under Steady Subsonic flow. The results were obtained for a wing planform with rectangular Cross section with a specified Aspect Ratio. The theoretical results for Lift, Drag are computed using VLM. The obtained theoretical results are compared with the experimental results.