ADJOINT-BASED AERODYNAMIC SHAPE OPTIMIZATION OF A STRAKE-DELTA WING CONFIGURATION

2021-11-8
Yutük, Kaan
Modern fighter aircraft compulsorily demand high maneuverability capability, which is mainly provided by an improved aerodynamic performance at high angles of attack. This is achieved by mostly employing strakes and canards. In this study, adjoint-based configuration and leading edge shape optimizations of a strake on a double-delta wing configuration are performed. SU2 is employed for flow and adjoint solutions. SU2 flow solutions are first verified on solutions for adaptive grids. In the configuration optimization, the sweep angle of the strake is considered as design variable. In the leading edge shape optimization, the free-form deformation box is employed. Remarkably, it is only allowed to modify the leading edge without changing the flat strake surface. Optimization studies are performed for both inviscid and turbulent flows at 10° and 22.5° angles of attack, respectively. It is shown that the sweep angle optimization based on turbulent flow solutions improves the L/D ratio by about 8.4% at 10° angle of attack and 2.7% at 22.5° angle of attack. In addition, the leading edge shape optimization based on turbulent flow solutions improves the L/D ratio by about 4.5% at 10° angle of attack and 3% at 22.5° angle of attack.

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Citation Formats
K. Yutük, “ADJOINT-BASED AERODYNAMIC SHAPE OPTIMIZATION OF A STRAKE-DELTA WING CONFIGURATION,” M.S. - Master of Science, Middle East Technical University, 2021.