Abstract
An aerodynamic optimization for a Droop-Nose Leading-Edge (DNLE) morphing of a well-known UAV, the UAS-S45, is proposed, using a novel Black Widow Optimization (BWO) algorithm. This approach integrates the optimization algorithm with a modified Class-Shape Transformation (CST) parameterization method to enhance aerodynamic performance by minimizing drag and maximizing aerodynamic endurance at the cruise flight condition. The CST parameterization technique is used to parameterize the reference airfoil by introducing local shape changes and provide skin flexibility to obtain various optimized morphing airfoil configurations. The optimization framework uses an in-house MATLAB algorithm, while the aerodynamic calculations use the XFoil solver with flow transition estimation criteria. These results are validated with a CFD solver utilizing the Transition (γ−Reθ) Shear Stress Transport (SST) turbulence model. Numerical studies verified the effectiveness of the optimization strategy, and the optimized airfoils have shown a significant improvement in overall aerodynamic performance by up to 12.18% drag reduction compared to the reference airfoil, and an increase in aerodynamic endurance of up to 10% for the UAS-S45 optimized airfoil configurations over its reference airfoil. These results indicate the importance of leading-edge morphing in enhancing the aerodynamic efficiency of the UAS-S45 airfoil.
Highlights
Rising fuel prices and increased environmental concerns have driven the aircraft manufacturing industry to set new goals for the future
This paper investigates suitable methods for the aerodynamic design of a Droop-Nose Leading-Edge (DNLE) morphing by employing modified Class-Shape Transformation (CST) for the aerodynamic shape optimization
The optimization results from coupling the CST parameterization methods with the Black Widow Optimization (BWO) algorithm for the UAS-S45 airfoil for the Droop-Nose Leading-Edge (DNLE) Morphing design were obtained
Summary
Rising fuel prices and increased environmental concerns have driven the aircraft manufacturing industry to set new goals for the future. Some well-known techniques for geometrical parameterization are presented in the literature [31,32] These methods have the disadvantages of not using airfoil shape parameters, requiring a large number of design variables, and frequently producing erroneous shapes for an airfoil’s leading and trailing edges. The geometry definition must be used together with an optimization technique that takes the airfoil parameterization into account Another novel approach of parameterization, known as Class-Shape Transformation (CST), is a highly effective parameterization method thanks to its simplicity, resilience, and capacity to categorize the aerodynamic shape in a variety of configurations. This paper investigates suitable methods for the aerodynamic design of a Droop-Nose Leading-Edge (DNLE) morphing by employing modified Class-Shape Transformation (CST) for the aerodynamic shape optimization. This work is part of the LARCASE Morphing Wing project, which addresses methods for UAS-S45 optimization
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