Payam Dehpanah, Scientific Computing Group, TU Kaiserslautern
Integrating Airfoil Optimal Design within the Blended-Wing-Body Conceptual Design Framework
The blended-wing-body configuration is introduced as the future airliner in recent decades. A quick computational airfoil design can assess design individuals in the design space. This study determines the possibility of integrating an optimal airfoil design within the blended-wing-body conceptual aircraft design framework. The continuous adjoint method for the Euler equations is developed within the conceptual design framework. The framework evaluates the configuration before and after the airfoil optimal design process. The airfoil aerodynamic design is studied for one symmetrical and two S-shaped airfoils with adequate thickness-to-chord ratio for the centerbody profile. Three sequential objective functions including lift, drag, and pitching moment are subjected to the design constraints. Projected aerodynamic performances of the optimized airfoils, including lift-to-drag ratio and static margin are acquired appropriately. In addition, off-design performance, including the RANS solutions, are studied. The result of the blended-wing-body conceptual design framework with optimized airfoils are evaluated.
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