For revealing the aerodynamic interaction mechanism between the rotor/fuselage/nacelle and wing of the tiltrotor aircraft

a CFD solution was established. The unstructured hybrid mesh system consist of triangular prism and tetrahedron meshes suitable for solving flowfield of tiltrotor aircraft under multiple flight conditions were established. Three-dimensional Navier-Stokes equations was the main control equation and the momentum source method was used to simulate the flowfield of tiltrotor

and data sharing OpenMP parallel strategy was employed to accelerate the calculation as well. A new momentum source adding and searching method was proposed. The aerodynamic interactions of tiltrotor/fuselage/nacelle on wing were simulated respectively

and some valuable conclusions for optimization were obtained. The surrogate model based on radial basis function (RBF) was used for the tiltrotor aerodynamic optimization problem. Considering the interaction effects on different sections of wing

the wing airfoils were used as the design variables in the optimization design process of tiltrotor aircraft

and optimized life/drag were improved by 36.78% compared with the original model.