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.

Journal Publications

Zha, G.-C., Smith, D., Schwabacher, M., Rasheed, K., Gelsey, A., Knight, D. D. and Haas, M., "High Performance Supersonic Missile Inlet Design Using Automated Optimization", AIAA Journal of Aircraft, Vol.34, No. 6, Nov.-Dec. 1997, p. 697-705

Conference Publications:

Zha, G.-C., Smith, D., Schwabacher, M., Rasheed, K., Gelsey, A., Knight, D. D. and Haas, M., "`High Performance Supersonic Missile Inlet Design Using Automated Optimization", AIAA Paper 96-4142, 1996,6th AIAA/NASA/ISSMO Symposium on Multidisciplinary Analysis and Optimization, Sept. 4-6, 1996