Steady/unsteady aerodynamic analysis of wings at subsonic, sonic and supersonic Mach numbers using a 3D panel method

Abstract

SUMMARYThis paper treats the kernel function of an integral equation that relates a known or prescribed upwash distribution to an unknown lift distribution for a ÿnite wing. The pressure kernel functions of the singular integral equation are summarized for all speed range in the Laplace transform domain. The sonic kernel function has been reduced to a form, which can be conveniently evaluated as a ÿnite limit from both the subsonic and supersonic sides when the Mach number tends to one. Several examples are solved including rectangular wings, swept wings, a supersonic transport wing and a harmonically oscillating wing. Present results are given with other numerical data, showing continuous results through the unit Mach number. Computed results are in good agreement with other numerical results.

Calculation of nonlinear aerodynamic characteristics of a wing using a 3‐D panel method

“…The purpose of the present research is to analyse the nonlinear aerodynamic characteristics of three-dimensional wing using the frequency-domain panel method [11,12]. The frequencydomain panel method uses the kernel function of an integral equation that relates a known or prescribed upwash distribution to an unknown lift distribution for a finite wing.…”