Based on the influence research of design parameters on the aerodynamic performance of two dimensional convergent and divergent (2D-CD) nozzle

the optimization design of 2D-CD nozzles' profile was conducted. The goal of optimization design was to get thrust coefficient as high as possible. The design variables of optimization design were throat aspect ratio

throat radius ratio

convergent half angle

divergent half angle. In the design process

the initial sample points were selected using the orthogonal experiment design method

then the Kriging surrogate model of thrust coefficient for design parameters was established. The analysis and optimization was conducted with the Adaptive Simulated Annealing Algorithm (ASA). The results show that when the throat aspect ratio is 6

throat radius ratio is 0.3

convergent half angle is 15°

divergent half angle is 5.64°

the maximum thrust coefficient of the 2D-CD nozzle is 0.97847

and the flow coefficient is 0.98778.