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Adjoint based optimization of supersonic converging diverging nozzle

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2019
Yerlikaya, Berkan
The nozzle produces the required thrust for the vehicle in an aircraft or rocket engine by expanding and accelerating the exhaust gas. In this study, the thrust of a supersonic converging-diverging nozzle is optimized by using SU2 software and the adjoint-based optimization tool. During the design optimization procedure, the inlet area, the exit area and the length of the nozzle are kept constant. The main objective is to obtain the maximum thrust within the geometric limitations. In order to maximize the thrust, the exit Mach number and the mass flow rate are selected as the objective functions. They are employed individually and in an equally weighted combination. The highest value in terms of thrust is achieved at the end of the unconstrained multi objective optimization study with low total pressure at the exit of the nozzle. Therefore, a total pressure value is assigned as a constraint to the multi objective optimization. Finally, thrust value is increased with establishing the desired total pressure recovery.