Optimization of aerodynamic shapes by means of inverse method

The aim of this work is the attainment of an efficient technique for modeling aerodynamic bodies submitted to flows at high speeds. The inverse method, based on the Elastic Membrane Technique, is used to find a new geometry. Pressure coefficient comes from the Euler equations is solved by the finite volume with explicit Runge-Kutta five-stages scheme. Numerical tests are carried out for NACA 0012, 0009 and a new geometry for Mach 0.8 using the Euler equations and the results are found to compare favorably with experimental or numerical data available in the literature. Besides, it is worth pointing out that the technique build on earlier ones, because the coefficients needed to do the optimization shape calculations are adequately calculated.