Transonic Aerodynamic Efficiency Assessment of an Optimised Supersonic Civil Transport using CFD.

摘要

This paper describes the effort undertaken at NLR to predict the aerodynamics efficiency of a supersonic civil transport aircraft design at transonic cruise. The aircraft design consists of a wing-fuselage combination, employing leading edge deflections and one deflected trailing edge flap to meet the transonic targets. A fuselage extension to mimic the wind tunnel model sting support is taken into account. The aerodynamic efficiency is predicted using a multi-block structured Navier-Stokes flow analysis system. Aerodynamic efficiency data at flight Reynolds number are obtained by CFD, using solution adaptive wall-normal grid spacin to adjust the boundary layer resolution. Also, the effect of the wind tunnel model sting support is investigated by additional computations on a similar configuration using the original upswept fuselage.