Aerodynamic performance plays a paramount role in the design of reusable winged space vehicle. To achieve appropriate level of aerodynamic quality, optimization methods coupled with CFD solvers could be applied. The article proposes the approach to selection and optimization of the airfoil for reusable space vehicle that operates at different speed regimes. The flow field was computed with a finite-volume CFD solver where the discrete adjoint approach is implemented. The comparison was done for three different airfoils at various angles of attack and the optimal one was chosen.
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