Using Existing Flow-Field Analysis Codes for Inverse Design of Three-Dimentional Aerodynamic Shapes
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This chapter demonstrates that it is possible to use existing proven arbitrary flow-field analysis codes without any modifications to perform inverse aerodynamic design of two-dimensional and three-dimensional shapes. A general concept for inverse design of aerodynamic shapes based on treating the aerodynamic surface as an elastic membrane subject to a specified surface pressure distribution is explained. A new mathematical formulation based on the Fourier series analytical solution of this model is detailed. The method is formulated for two-dimensional and for three-dimensional configurations. It can be used in conjunction with any available flow-field analysis code without a need for modification of such a code. Preliminary testing of the new method is performed with a potential flow surface panel code, an Euler flow solver, and a Navier-Stokes flow solver. The convergence rate of the design process is found to be similar for both non-lifting and lifting aerodynamic shapes with the Navier-Stokes flow solver typically requiring minimum number of design iterations. Suggestions for further research and improvements are made.
KeywordsElastic Membrane Degree Angle Inverse Design Aerodynamic Shape Airfoil Shape
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