Numerical Simulation of Supersonic Flow around Wing-Body Configuration with Integrated Engine Nacelle

Abstract

This paper presents numerical simulation of flowfields around a supersonic transport aircraft with integrated engine nacelles. In this study, flowfields were simulated by solving the Euler equations with the unstructured grid method for handling the complex geometry. To simulate intake flows at actual flight conditions, a bump was introduced inside the nacelle. The effect of nacelle mass flow ratios on overall aerodynamic performance was investigated in detail by changing bump heights. The spillage drag was calculated and found to have a large impact on the total drag. Computed results showed excellent agreements with wind tunnel data obtained at National Aerospace Laboratory of Japan.