Study on Aerodynamic Shape Optimization of Supersonic Low-Boom Aircraft Considering Dynamic Effects

Supersonic civil aircraft has revolutionized the commuting efficiency of civil aviation, and has become an important strategic means of transportation in the background of economic globalization. The primary task of developing a new generation of supersonic civil aircraft is to overcome the obstacles of the sonic boom. In order to obtain the influence of the engine system on the design guidelines for low sonic boom, a optimization method based on the flow field/sonic boom coupled adjoint equation was proposed. Research has shown that the powered nacelles will lead to a stronger near-field spatial wave system, with the enhancement of the tail shock wave. After optimization, the sonic boom intensity of the shape with through-flow nacelles was reduced by 16.95 PLdB, while the sonic boom intensity of the shape with powered nacelles was reduced by 9.09 PLdB, indicating that the discrete adjoint optimization method used can effectively carry out the optimization design of typical supersonic civil aircraft shapes considering the influence of power. Under the same initial conditions, the design parameters of the powered nacelle configuration are more sensitive. The optimized configuration of the powered nacelle moves more up the wing root position, has a greater curvature of the flat tail wing shape, and the curvature of the upper and lower surfaces of the fuselage is also more pronounced.