TY - GEN
T1 - Airfoil Design Framework for Optimized Boundary-Layer Parameters
AU - Garcia, Armando R.Collazo
AU - Ansell, Phillip J.
N1 - Publisher Copyright:
© 2022, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2022
Y1 - 2022
N2 - An airfoil design method is proposed which considers the boundary-layer integral parameters as the driving design condition. The method consists of a parameterization for generation of a pressure distribution capable of producing desired boundary-layer characteristics, which is then used to obtain a corresponding airfoil geometry through an inverse design approach. More specifically, the pressure distribution that results in the minimum θT E condition is considered since, by deduction from the Squire-Young theory, it would produce the minimum drag. As a case study, the LRN1015 airfoil was considered as a seed geometry and modified based on the mission requirements of the RQ-4B Global Hawk. Numerical results obtained using a viscous-inviscid Euler simulation showed that the optimized airfoils achieved Cd reductions of 9.06% and 6.00%, respectively, for the α = 0◦ and L/Dmax design points considered.
AB - An airfoil design method is proposed which considers the boundary-layer integral parameters as the driving design condition. The method consists of a parameterization for generation of a pressure distribution capable of producing desired boundary-layer characteristics, which is then used to obtain a corresponding airfoil geometry through an inverse design approach. More specifically, the pressure distribution that results in the minimum θT E condition is considered since, by deduction from the Squire-Young theory, it would produce the minimum drag. As a case study, the LRN1015 airfoil was considered as a seed geometry and modified based on the mission requirements of the RQ-4B Global Hawk. Numerical results obtained using a viscous-inviscid Euler simulation showed that the optimized airfoils achieved Cd reductions of 9.06% and 6.00%, respectively, for the α = 0◦ and L/Dmax design points considered.
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U2 - 10.2514/6.2022-3214
DO - 10.2514/6.2022-3214
M3 - Conference contribution
AN - SCOPUS:85186317576
SN - 9781624106354
T3 - AIAA AVIATION 2022 Forum
BT - AIAA AVIATION 2022 Forum
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA AVIATION 2022 Forum
Y2 - 27 June 2022 through 1 July 2022
ER -