Transonic Flow Past Conically Cambered Wings

Abstract

The flow is analysed over conically cambered wings for transonic flow conditions. Wing Planform is conically cambered for supersonic flow for minimum induced drag.  The circulation to determine the forces is developed using panel methods. Objective function for drag minima is formed using Lagrange multipliers. The transonic flow computations are progressed through computational fluid dynamics. In case of a subsonic leading edge in supersonic flow there is no shock wave that appears over the wing, whether the wing is non-optimal or optimally cambered. This is advantageous towards optimization. The tip region is seen to have appreciable difference in nature of pressure distribution for these two cases over the entire chord length.

Keywords: transonic flow, wings, drag