Efficient and Refined Transonic Flow Analysis Using a New Flux Vector Splitting Scheme

Abstract

A still pending design problem is the aerodynamic shaping of wing-fuselage junctions with possibly lowest transonic drag particularly for transport aircraft. In the present work the fluid dynamic physics of the transonic flow at the nose region of wing roots are investigated numerically in order to get more insight into the potential of aerodynamic shape optimization and its limitations by flow physics. The method applied for this purpose is a CFD-code equipped with a new flux vector splitting scheme (FVS) based on a reference speed deviating from the speed of sound. The reason for the introduction of the present FVS is its capability of handling flow problems covering the speed range from extreme low to extreme high without preconditioning, a highly welcome feature in industrial aerodynamics simulation. For reducing computer residing time a nested loop minimum residual driver has been developed requiring considerably less storage than needed by standard general minimum residual methods (GMRES).