Assessment of a Hybrid Delta Wing Vortex Flow Investigation – Part II at Transonic Conditions

Abstract

This paper provides an overview of a set of computational fluid dynamical (CFD) calculations performed within NATO-STO AVT-316 on a hybrid delta wing test geometry at transonic conditions. The cases cover a range of angles of attack from low, but challenging, to high and very non-linear. The transonic flow regime for this configuration is complex, involving vortex-surface, vortex-vortex and shock-vortex interactions. The performance of three turbulence models is examined: SSG-LRR, the explicit algebraic Reynolds stress model (EARSM) of Wallin & Johansson, and the Menter SST model (with and without rotation correction). These are assessed by comparison of pressure distributions, and aircraft forces and moments, against wind-tunnel data, with particular regard to the capture of characteristics relevant to aircraft design. The SSG-LRR model was found to provide the best predictive capability, taking an overall account of force, moment and surface pressure predictions.