Application of HOSVD to Aerodynamics. The Problem of Shock Waves

Abstract

Efficient interpolation in aerodynamic databases is important for the aeronautic industry because of its implication on both the cost and time needed to complete design cycles. In this study a method based on high-order singular value decomposition is presented focusing on the problems associated with the shock wave like structures that do not suit well with this kind of methods. To illustrate the methodology, the flow around a two-dimensional airfoil is considered at a Reynolds number of 20 × 106 with three free parameters, namely, the Mach number, the angle of attack, and the flap deflection angle in the ranges of [0.4, 0.8], [¿3º, 3º], and [¿5º, 5º], respectively. The method is robust in the sense of being able to deal with very different flow topologies.