An integrated optimization for hypersonic inlet design based on PYTHON

In this paper, an integrated optimization program, based on PYTHON script programming language, has been developed by integrating CFD software and optimization package for shape optimization of high speed flight vehicles. The program comprises four functions connected with PYTHON scripts: geometry module, flow grid generator, flow solver, and optimizer, and the data of each part can be exchanged and updated automatically until the iterative study is completed. The paper takes two-dimensional hypersonic inlet with planar lip as an example for design and analysis. The numerical results show that the boundary-layer separation caused by shock boundary-layer interaction in the shoulder of inlet is reduced significantly and the total pressure recovery coefficient of the inlet is greatly improved against the model before optimized. With the increase in computer performance, the integrated optimization coupling with CFD technology will be the trend for vehicle design with aerodynamics in the future.