ADJOINT BASED AERODYNAMIC SHAPE OPTIMIZATION OF A MISSILE ENGINE INLET COVER

Date

2024-6-27

Author

Özuzun, Arda

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This thesis addresses the aerodynamic shape optimization of a missile engine inlet cover, a component designed to prevent windmilling on the gas turbine engines during the gliding phase of the missiles. The adjoint-based optimization is conducted with the open-source SU2 software suite. The cover shape is controlled by means of a Free Form Deformation box control points. The design objectives are to minimize the drag and maximize the opening moment of the inlet cover at the same time. Both single and multi-objective optimizations with weight factors are performed. The findings are discussed in detail, and it is shown that the optimization process provides new cover shapes for increased aerodynamic performance compared to the quarter-spherical baseline cover.

Subject Keywords

Computational Fluid Dynamics, Aerodynamic Shape Design, Adjoint Based Optimization, Free Form Deformation Box, SU2

URI

https://hdl.handle.net/11511/110162

Collections

Graduate School of Natural and Applied Sciences, Thesis