Abstract
Conversion of a general three-dimensional linear unsteady aerodynamic software system to a configuration shape sensitivity code for planar-lifting-surface configurations at subsonic, sonic, supersonic, and hypersonic flows is described. This was achieved by the accomplishment of the following: A global shape design variable sensitivity scheme was formulated based on the complex variable differentiation (CVD) technique. The CVD technique was incorporated into the software system for shape sensitivity analysis. The new capability was validated with the finite difference method and parametric studies on an AGARD swept wing, AGARD wing‐tail configuration, a 60-deg swept wing, and an F-5 wing with a control surface. This selection of test cases covers subsonic to hypersonic planar cases in which singularities in the integrals involved are strong, with aerodynamic interference between lifting surfaces, and including supersonic cases with discontinuous pressure distributions. The most challenging aspects of shape sensitivity analysis for linear unsteady aerodynamics have, thus, been addressed.
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