Aerodynamic Design Optimization

The automated design optimization is used to design a ramjet missile inlet at Mach 4.0. A multi-level analysis strategy is used to save the CPU and turn-around time. An efficient empirical code is incorporated to an Genetic Algorithms optimizer to locate the area of the global optimum and a gradient based optimizer is used to search the final optimum design. The total pressure recover is drastically improved and the design cycle is significantly reduced.

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