Calculation of Aerodynamic Sensitivities by Boundary-Integral Methods and Application to Lifting-Surface Theory
Methodology for analytically generating the aerodynamic sensitivities (rates of change of surface pressures and aerodynamic coefficients with respect to changes in aircraft geometry), needed in aerodynamic shape optimization and multidisciplinary design synthesis, has been derived and illustrated with lifting-surface theory. The arbitrary continuous or discontinuous global or local perturbation is defined in terms of a single variable. The procedure is adaptable to surface-panel and even nonlinear integral methods without the prohibitively expensive perturbation of each panel node as proposed by others.
KeywordsMach Number Boundary Element Method Unsteady Flow Subsonic Flow Local Perturbation
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