An　approach　for　the　aerodynamic　optimization　design　of　elastic　configuration　is　implemented　and　tested.　Aeroelastic　analysis　was　carried　out　by　coupling　Euler　equations　solver　and　finite-element　structural　solver.　Two　important　techniques　used　in　high-fidelity　aerostructural　design　optimization　are　discussed,　which　are　the　grid　deformation　method　and　the　update　method　of　finite-element　mesh　(FEM).　An　improved　grid　deformation　methodology　based　on　transfinite　interpolation　(TFI)　and　radial　basis　function　(RBF)　method　is　presented,　which　adapts　to　complex　configuration　very　well.　The　technique　to　update　the　FEM　is　based　on　bilinear　interpolation　method　and　RBF　method,　and　it　adapts　to　any　grid　type　of　finite-element　model.　Discrete　adjoint　method　is　used　to　get　the　gradient　of　objective　function　with　respect　to　design　variables.　Optimizations　of　a　wing　and　a　more　realistic　wing-body　configuration　are　done　to　demonstrate　the　effectiveness　of　the　proposed　approach.　Results　show　that　the　lift　to　drag　ratio　can　be　improved　with　constraints　through　optimization,　which　indicates　that　the　present　methodology　can　be　successfully　applied　to　the　optimization　design　of　transonic　jig　shape　of　aircraft.　©　2012　AIAA.