Abstract
A discrete adjoint solver is developed from an unstructured cell-vertex finite-volume Navier-Stokes solver for efficient aerodynamic design optimization. All the differentiations are made by hand. The adjoint code is verified by comparison of flux Jacobian and objective function gradient with finite differences. An aerodynamic design tool is developed combining the flow solver, adjoint solver, volume mesh modification routine and a gradient-based optimizer. Hicks-Henne shape functions are adopted for the surface geometry purterbation and a spring analogy method is employed for the volume mesh modification during the design process. The design tool is successfully applied to a design example of ONERA M6 transonic wing design.
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