Aerodynamic Optimization Design of Supersonic Wing Based on Discrete Adjoint

Reducing fuel consumption and improving the economy by effectively reducing cruising drag is main objective of aerodynamic design supersonic civil aircraft. In this paper, optimization system based on Reynolds-Averaged Navier–Stokes (RANS) equation discrete adjoint theory applied to wing design. Based system, a single-point study reduction in cruise conditions was carried out for two typical layouts, subsonic leading edge edge, reached 3.78% 4.53%, respectively. The characteristics different types wings were explored from perspectives load, twist angle distribution, pressure airfoil shape characteristics, flow field characteristics. results show that configuration dominated induced drag, while optimizer mainly focuses shock wave configuration. By comparing sensitivity analysis lift coefficients deformation with results, optimized dominant directions are qualitatively analyzed. derivatives obtained equations useful elaborate tendency reason trade-off generation under specific layouts engineering constraints, which provides reference future.