Determination of aerodynamic sensitivity coefficients based on the transonic small perturbation formulation

The quasianalytical approach is developed to compute airfoil aerodynamic sensitivity coefficients in the transonic and supersonic flight regimes. Initial investigation verifies the feasibility of this approach as applied to the transonic small perturbation residual expression. Results are compared to those obtained by the direct (finite difference) approach, and both methods are evaluated to determine their computational accuracies and efficiencies