Abstract
The Aerodynamic Shape Optimizer for Rotor Blades (ADSORB) framework was used to perform four case studies optimizing the UH-60A blade airfoils along the blade span. The framework is built within Galaxy Simulation Builder. It uses CFD to generate data and construct a surrogate model for airfoil coefficient predictions. Dakota and a multiobjective genetic algorithm are then used to optimize the blade airfoils for four distinct segments of the blade. RCAS was then used to predict the rotor power in hover and forward flight (advance ratio 0.3), as well as the rotor L/DE in a high load forward flight condition (CT/σ ≈ 0.13). Each case study compared different combinations of objective functions to determine the most desirable traits. Ultimately, a design was found that increased the high load L/DE by 6.7%, while decreasing the hover and forward flight rotor power by 2.0% and 2.7%, respectively.
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