TY - GEN
T1 - Design of an airfoil morphing leading edge for high-lift applications using a genetic algorithm
AU - Colletti, Christopher R.
AU - Ansell, Phillip J.
N1 - Publisher Copyright:
© 2021, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2021
Y1 - 2021
N2 - A genetic algorithm was used to design a morphing leading-edge shape on a slotted natural laminar flow airfoil in order to maximize the airfoil while retaining a constant leading-edge arc length. The MSES program suite was used to evaluate a randomized population of airfoils during the design process at freestream conditions of M = 0.225 and Re = 16×106 to match the low-speed, high-lift conditions for a representative single-aisle commercial transport aircraft. By using different definitions of the objective cost function, multiple airfoil designs were found through the genetic algorithm to create a library of possible designs. MSES simulations conducted on the selected airfoil design currently envisaged for the high-lift application were found to have a of 2.56 at an angle of attack of 23.0°. Additional variants of the airfoil were also produced to purposefully alleviate the leading-edge stall tendencies of the baseline airfoil.
AB - A genetic algorithm was used to design a morphing leading-edge shape on a slotted natural laminar flow airfoil in order to maximize the airfoil while retaining a constant leading-edge arc length. The MSES program suite was used to evaluate a randomized population of airfoils during the design process at freestream conditions of M = 0.225 and Re = 16×106 to match the low-speed, high-lift conditions for a representative single-aisle commercial transport aircraft. By using different definitions of the objective cost function, multiple airfoil designs were found through the genetic algorithm to create a library of possible designs. MSES simulations conducted on the selected airfoil design currently envisaged for the high-lift application were found to have a of 2.56 at an angle of attack of 23.0°. Additional variants of the airfoil were also produced to purposefully alleviate the leading-edge stall tendencies of the baseline airfoil.
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M3 - Conference contribution
AN - SCOPUS:85100301083
SN - 9781624106095
T3 - AIAA Scitech 2021 Forum
SP - 1
EP - 16
BT - AIAA Scitech 2021 Forum
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2021
Y2 - 11 January 2021 through 15 January 2021
ER -