Incompressible flow past oscillatory wings of low aspect ratio by the integral equations method

In the framework of the linearized perturbation theory, the pressure jump over the oscillating wing is the solution of a two-dimensional integral equation. Performing an asymptotic expansion with respect to the aspect ratio and keeping the leading terms, we reduce the integral equation to a one-dimensional one, obtaining a simpli ed method of solving the lifting surface integral equation for a class of thin wings of low aspect ratio with a straight trailing edge. The one-dimensional integral equation is solved for the delta at plate and the pressure coe cient eld and the lift and moment coe cients are calculated. The range of validity of the new method is discussed in the nal part of the paper