With restart global algorithm and Gaussian process(GP) model

supersonic nozzle contour optimization was investigated to improve the flow quality in test section. According to the experimental results in 06m continuous transonic wind tunnel

the optimization problem was defined and the CFD results were verified. The crowding distance notation was introduced to form a restart mechanism for a highly efficient global algorithm. The relationship between design parameters and aerodynamic performances was modeled with Gaussian process model

and used in optimization as a surrogate for the real evaluation procedure to reduce the number of CFD evaluation. Result shows that the optimization framework can improve supersonic nozzle performance efficiently

the root mean square deviation of Mach number in model area falls from 0.012 to 0.001

and axial gradient of Mach number falls from 0.049 to 0.