Aerodynamic Design and Verification of a Low-Boom Supersonic Jet

Based on the conceptual scheme of the Chinese Aeronautical Establishment–Quiet Supersonic Business Jet (CAE-QSBJ), a wing-body-tail assembly without canards is selected as the research configuration C01. Design method for supersonic civil aircraft coupled with improved fast sonic boom prediction method, high-precision sonic boom prediction method, and inverse design based on the equivalent cross-sectional area were proposed, related numerical tools/modules were improved and integrated into a design/analysis framework. The refined scheme C02 focused on optimizing wing parameters to weaken the shock wave intensity of the high-pressure regions on the inboard-outboard wings and fuselage, resulting in a 4.85 PLdB reduction in the ground sonic boom loudness compared with Scheme C01. In the inverse design study, the distribution of the target equivalent cross-sectional area was parameterized, and the cross-sectional area distribution of each part of the fuselage was dynamically optimized to match the target, the intensity of the ground sonic boom signal of Scheme C03 was further reduced by 3.84 PLdB compared with Scheme C02. Finally, the performance of configuration C03 were verified through force measurement wind tunnel tests and sonic boom characteristic tests, which also demonstrated the effectiveness of the present aerodynamic design method for low sonic boom supersonic civil aircraft.