Abstract
In deriving automatic numerical optimization algorithms for aerodynamic applications, the design parameters are usually chosen to be the unknown airfoil/blade profiles. However, there are certain advantages in using the pressure/velocity distribution as the design variable in some applications; the designed distribution can then be used in a 3D inverse design method to generate the actual profile shape. Here, this approach will be addressed. Two methods are used to parametrize the circulation distribution for compressor blades. Dawes’s code is used to predict the viscous effect. An automatic optimization algorithm is developed to minimize the loss with respect to the design parameters.
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