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Sensitivity analysis and optimization of delta wing design parameters using CFD-based response surface method
Author(s): Mohammad Aelaei, S. Karimian Aliabadi, Fathollah Ommi
Keywords: Delta wing, Air launch-to-orbit vehicle, aerodynamic efficiency, NSGA-II Optimization, Response Surface Methodology
This paper explores the effect of design variables on the objective functions of clipped delta wing with a modified double-wedge airfoil section based on parametric analysis and CFD-based optimization using response surface method. This type of wing is used in air-launch-to-orbit vehicles. The thickness, wing-span, tip chord, leading edge radius, forward diagonal edge and aft diagonal edge lengths are defined as design variables and aerodynamic efficiency, drag and lift coefficients as objective functions. The analysis was performed at Mach 0.85 and 1.2 and for several AOA. The total number of 368 problems have been numerically solved as a basis for construction of a generalized response surface. Minimizing the drag force and maximizing both lift coefficient and aerodynamic efficiency have been selected as optimization goal. The evolutionary optimization technique of NSGA-II in combination with the RSM has been used, which leads to distinct but very close candidates for each flight conditions. Defining the critical design point, it can be deduced the aerodynamic efficiency will be increased by 50% compared with base wing model. Finally, it is shown that the best point for optimizing the air-launched vehicle equipped with delta wing in the ascent trajectory, is the maximum AOA that occurs at Mach 1.2.