A numerical simulation of flowfields around a supersonic transport aircraft with integrated engine nacelles is presented. 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 throat was introduced inside the nacelle. The effect of nacelle mass flow ratios on overall aerodynamic performance was investigated in detail by changing throat heights. The spillage drag was calculated and found to have a large impact on the total drag. Computed results showed excellent agreement with wind-tunnel data obtained at the National Aerospace Laboratory of Japan.
ASJC Scopus subject areas
- Aerospace Engineering