TY - JOUR
T1 - Shape optimization of rotorcraft airfoils using a genetic algorithm
AU - Stanko, Jason D.
AU - Coder, James G.
AU - Schmitz, Sven
N1 - Funding Information:
The authors are grateful to the US Army’s National Rotorcraft Technology Center program for funding this research. Effort sponsored by the US Government under Other Transaction number W15QKN-10-9-0003 between Vertical Lift Consortium, Inc. and the Government. The US Government is authorized to reproduce and distribute reprints for Governmental purposes notwithstanding any copyright notation thereon. The views and conclusions contained herein are those of the authors and should not be interpreted as necessarily representing the official policies or endorsements, either expressed or implied, of the US Government.
Funding Information:
The authors are grateful to the US Army's National Rotorcraft Technology Center program for funding this research. Effort sponsored by the US Government under Other Transaction number W15QKN-10-9-0003 between Vertical Lift Consortium, Inc. and the Government. The US Government is authorized to reproduce and distribute reprints for Governmental purposes notwithstanding any copyright notation thereon. The views and conclusions contained herein are those of the authors and should not be interpreted as necessarily representing the official policies or endorsements, either expressed or implied, of the US Government.
Publisher Copyright:
Copyright © 2018 by AHS International, Inc. All rights reserved.
PY - 2018
Y1 - 2018
N2 - In this work, a genetic algorithm was implemented to perform an airfoil shape optimization with constraints applied to the airfoil cross-sectional area and pitching-moment coefficient. Constraints are enforced through the use of an augmented Lagrange penalty function. The design variables are formed through a class shape transformation approach with orthogonal, polynomial basis modes. The use of an orthogonal basis provides decreased levels of multicollinearity in higher-order design spaces, while still maintaining the completeness of lower-order spaces. The optimization methodology is demonstrated on the tip airfoil of a UH-60A baseline rotor. The design trade-offs of a new tip airfoil are investigated where the optimized tip section shows improvements in forward-flight performance in exchange for a small reduction in the rotor's stall margin.
AB - In this work, a genetic algorithm was implemented to perform an airfoil shape optimization with constraints applied to the airfoil cross-sectional area and pitching-moment coefficient. Constraints are enforced through the use of an augmented Lagrange penalty function. The design variables are formed through a class shape transformation approach with orthogonal, polynomial basis modes. The use of an orthogonal basis provides decreased levels of multicollinearity in higher-order design spaces, while still maintaining the completeness of lower-order spaces. The optimization methodology is demonstrated on the tip airfoil of a UH-60A baseline rotor. The design trade-offs of a new tip airfoil are investigated where the optimized tip section shows improvements in forward-flight performance in exchange for a small reduction in the rotor's stall margin.
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M3 - Conference article
AN - SCOPUS:85054554343
SN - 1552-2938
VL - 2018-May
JO - Annual Forum Proceedings - AHS International
JF - Annual Forum Proceedings - AHS International
T2 - 74th American Helicopter Society International Annual Forum and Technology Display 2018: The Future of Vertical Flight
Y2 - 14 May 2018 through 17 May 2018
ER -