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Calculation of Aerodynamic Sensitivities by Boundary-Integral Methods and Application to Lifting-Surface Theory

  • E. Carson YatesJr.
  • Robert N. Desmarais
Conference paper

Abstract

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.

Keywords

Mach Number Boundary Element Method Unsteady Flow Subsonic Flow Local Perturbation 
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References

  1. 1.
    Hawk, J. D.; and Bristow, D. R., Development of MCAERO Wing Design Panel Method With Interactive Graphics Module. NASA CR-3775 (1984).Google Scholar
  2. 2.
    Yates, E. C., Jr., A Kernel-Function Formulation for Nonplanar Lifting Surfaces Oscillating in Subsonic Flow. AIAA Journal, Vol. 4, No. 8, pp. 1486–1488 (1966).CrossRefMATHADSGoogle Scholar

Copyright information

© Springer-Verlag Berlin Heidelberg 1990

Authors and Affiliations

  • E. Carson YatesJr.
    • 1
  • Robert N. Desmarais
    • 1
  1. 1.NASA Langley Research CenterHamptonUSA

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