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

Abstract

SUMMARYIn 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 simpliÿed 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 ÿeld and the lift and moment coe cients are calculated. The range of validity of the new method is discussed in the ÿnal part of the paper.

Subsonic Flow over a Thin Airfoil in Ground Effect

“…Additionally, he studied the aero-elastic stability of wing structures using continuum models. Besides the work of Balakrishnan, there has been a series of recent mathematical works (see for example: [9,10,15,21,27,28,34]) which have studied the mathematical aspects (existence, uniqueness, obtaining solutions, and stability) of different aerodynamic and aeroelastic problems. In conclusion, implementation of analytical techniques, despite their limitation and complexity, is significant in studying different aerodynamic and aeroelastic phenomena.…”