Abstract
DOI: 10.2514/1.24859 A continuous adjoint approach to aerodynamic design for viscous compressible flow on unstructured grids is developed. Sensitivity gradients arecomputed using tools ofshapedeformation of boundaryintegrals. Theresulting expressions involve second-order derivatives of the flow variables that require numerical solvers with greater than second-order accuracy. A systematic way of reducing the order of these terms is presented. The accuracy of the sensitivity derivatives is assessed by comparison with finite-difference computations, and the validity of the overall methodology is illustrated with several design examples.
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