Application of an hybrid optimization approach in the design of long endurance airfoils

Khurana, M 2008, 'Application of an hybrid optimization approach in the design of long endurance airfoils', in I Grant (ed.) Proceedings of the 26th Congress of the International Council of the Aeronautical Sciences, Alaska, United States, 14-19 September, 2008, pp. 1-13.


Document type: Conference Paper
Collection: Conference Papers

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Title Application of an hybrid optimization approach in the design of long endurance airfoils
Author(s) Khurana, M
Year 2008
Conference name 26th Congess of the International Council of the Aeronautical Sciences
Conference location Alaska, United States
Conference dates 14-19 September, 2008
Proceedings title Proceedings of the 26th Congress of the International Council of the Aeronautical Sciences
Editor(s) I Grant
Publisher American Institute of Aeronautics and Astronautics
Place of publication United States
Start page 1
End page 13
Abstract Future Re-Configurable Multi Mission Unmanned Aerial Vehicle (RC-MM-UAV) Design concepts are expected to comprise of morphing wings with mission segment based airfoils. The Direct Numerical Optimization (DNO) methodology for airfoil shape optimization is established. The PARSEC shape function is used for airfoil geometry parameterization, coupled with a low-fidelity solver and Particle Swarm Optimizer (PSO) in the design analysis of a long endurance airfoil. A single-point airfoil design study through the DNO approach was executed. Results indicate that the methodology is computationally demanding thus, Artificial Neural Networks (ANN) are introduced to address this issue. A relationship between PARSEC airfoil geometry variables as inputs and the equating aerodynamic coefficients as outputs are used in network training and validation. The effect of varying training sample size was evaluated to establish a network with acceptable generalization capabilities. The PSO model is integrated to the ANN model for airfoil design optimization. The hybrid PSO/ANN structure required 38% fewer solver calls in comparison to the direct search approach. The proposed hybrid methodology is applicable for future multi-point airfoil design optimizations.
Subjects Aerospace Structures
Keyword(s) airfoil design
diect numeric optimisation
neural networks
Copyright notice © Manas Khurana
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