Aerodynamic design and performance analyses of grid fin in supersonic flow using design of experiments and computational fluid dynamics

Dinçer, Erdem
Control surfaces are key components of missile aerodynamic performance that can create the necessary forces and moments to make maneuvers. Grid fins are unconventional control surfaces used for aerodynamic control of missiles. In this thesis, parametric design of grid fin is performed in terms of aerodynamic performance using Design of Experiments and Computational Fluid Dynamics. The 3-D, steady-state, compressible, viscous flow CFD simulations are performed for the complex grid fin geometries in supersonic conditions, using polyhedral unstructured grids. Design of Experiments method is used to reduce the number of computationally expensive and time-consuming CFD analyses. First, a validation study is performed for the CFD simulations using MICOM grid fin test case. Then, the aerodynamic performances of different grid fin designs are investigated using design parameters as chord, span, width, gap between members, web thickness, and frame thickness. Grid fin geometries are investigated at Mach number of 2.5 for different angles of attack between 0° and 15° and for roll angles of 0° and 45° at sea level standard atmospheric conditions. In parameter screening results, it is shown that the normal force, side force, and roll moment coefficients do not affected by the frame and web thickness parameters. Response surfaces are validated and can be used for optimization studies of grid fin. High chord-to-gap ratio decreases the aerodynamic performance which is caused by the separation in higher angles of attack values. Also, the change in the roll angle influences the flow behavior which affects the aerodynamic performance of grid fins.


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Citation Formats
E. Dinçer, “Aerodynamic design and performance analyses of grid fin in supersonic flow using design of experiments and computational fluid dynamics,” M.S. - Master of Science, Middle East Technical University, 2022.