Aerodynamic shape optimization is carried out for (a) maximizing lift coefficient, Cl and (b) maximizing endurance factor (Cl3/2/Cd) of an airfoil at a transitional low Reynolds number (Re = 5 × 104) using surrogate-based optimization technique. Bezier curves are used to parameterize the airfoil. Latin hypercube sampling (LHS) technique is used to sample the initial set of samples. The aerodynamic response is estimated using low- and high-fidelity datasets. A co-kriging-based multi-fidelity surrogate is built using these datasets, and the response surface is used in the optimization procedure for the search of optima. Expected improvement strategy is used to update the surrogate at every iteration, and optimization is terminated once the convergence criterion is met. The objective function improvement for maximizing Cl and maximizing (Cl3/2/Cd) is 18.08% and 38.70%, respectively.
Multi-fidelity Aerodynamic Optimization of an Airfoil at a Transitional Low Reynolds Number
Lect.Notes Mechanical Engineering
Design and Development of Aerospace Vehicles and Propulsion Systems ; Chapter : 18 ; 239-252
2021-03-19
14 pages
Article/Chapter (Book)
Electronic Resource
English
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