Surrogate Based Shape Optimization of a Low Boom Fuselage Wing Configuration

Abstract

The appeal of a future supersonic transport aircraft for potential operators as well as broad acceptance by the general public is strongly influenced by the loudness of the sonic boom and the drag of the aircraft. In this paper a fuselage wing configuration is optimized using a surrogate based optimization method. The JAXA Wing Body configuration from the Second Sonic Boom Prediction Workshop is used as the reference geometry. The influence of different wing geometries on the drag and the loudness is assessed with a particular focus on the off-track loudness. The optimization process includes high-fidelity near-field Euler simulations with the DLR TAU code and a propagation algorithm based on the TRAPS code. The maximum level of perceived loudness for different off-track angles as well as the drag coefficient are used as objective functions for a multi-objective optimization. During the optimization the lift is kept constant by using the grid deformation technique.