Abstract
This paper presents a gradient-based optimal design procedure using a Continuous Sensitivity Equation method for shape parameters and a NURBS representation of the geometry. Derivatives of the objective functions needed by the optimizer are computed from the ow sensitivities. The methodology for handling parameter dependent boundaries is presented. The geometric representation and parametrization of airfoils is based on NonUniform Rational B-Spline (NURBS) which reduces the number of design variables needed to accurately represent a wing section while ensuring good smoothness properties. The proposed approach is rst veri ed on a problem with a close form solution. Then, the optimal gradient-based design procedure is applied to the optimal design of airfoils at low Reynolds number represented by NURBS using ten control points.
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