A rapid quasi-analytical method — low order
perturbation panel method — is presented for
calculating aerodynamic sensitivity derivatives for
subsonic wings. The method is based on the low order
panel method with the internal Dirichlet problem
formulation and analytical differentiations cascaded
and inverted. In terms of doublet strength
sensitivity to configuration geometry, the computing
cost of the present method for the partial
derivative matrix calculation is less than one order
of magnitude than the existing high order
perturbation panel method, but the accuracy is
comparable. Furthermore, by applying a physical
interpolation instead of a weighted geometrical
interpolation, the sensitivity derivatives of
pressure, lift and pitching moment coefficient with
respect to configuration geometry are derived and
calculated in the present paper. Such sensitivity
derivatives are lacking in high order perturbation
panel method. A few calculative examples are
given.