The quasi-analytical 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. The quasi-analytical approach is shown to be superior and worth further investigation.
Determination of aerodynamic sensitivity coefficients in the transonic and supersonic regimes
01.01.1989
Aufsatz (Konferenz)
Keine Angabe
Englisch
British Library Conference Proceedings | 1994
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