Aerodynamic design optimization of transonic natural-laminar-flow airfoil at low Reynolds number
type: Item
instance of: scholarly article
title: Aerodynamic design optimization of transonic natural-laminar-flow airfoil at low Reynolds number
zbMATH Open document ID: 1459.74155
DOI: 10.1155/2020/5812129
author: D. Kharzeev
published in: Mathematical Problems in Engineering
publication date: 2020-07-30T00:00:00Z
review text: Summary: The position and size of laminar separation bubble on airfoil surfaces exert a profound impact on the efficiency of transonic natural-laminar-flow airfoil at low Reynolds number. Based on the particle swarm algorithm, an optimization methodology in the current work would be established with the aim of designing a high and robust performance transonic natural-laminar-flow airfoil at low Reynolds number. This methodology primarily includes two design processes: a traditional deterministic optimization at on-design point and a multi-objective of uncertainty-based optimization. First, a multigroup cooperative particle swarm optimization was used to obtain the optimal deterministic solution. The crowing distance multi-objective particle swarm optimization and the non-intrusive polynomial chaos expansion method were then adopted to determinate the Pareto-optimal front of uncertainty-based optimization. Additionally, the \(\gamma- \overline{\operatorname{Re}}_{\theta t}\) transition model was employed to predict the laminar-turbulent transition. Regarding to the established optimization methodology, a propeller tip airfoil of solar energy unmanned aerial vehicle was finally designed. During optimization processes, the minimized pressure drag was particularly chosen as the optimization objective, while the friction drag increment served as a constraint condition. The deterministic results indicate that the optimized airfoil has a good ability to control the separation and reattachment positions, and the pressure drag can be greatly reduced when the laminar separation bubble is weakened. The multi-objective results show that the uncertainty-based optimized airfoil possesses a significant robust performance by considering the uncertainty of Mach number. The findings evidently demonstrate that the proposed optimization methodology and mathematical model are valuable tools to design a high-efficiency airfoil for the propeller tip.
Mathematics Subject Classification ID: 74P10
Mathematics Subject Classification ID: 74F10
Mathematics Subject Classification ID: 76H05
Mathematics Subject Classification ID: 49N90
zbMATH DE Number: 7226147
MaRDI profile type: Publication
full work available at URL: https://doi.org/10.1155/2020/5812129
OpenAlex ID: W3043719037
cites work: Optimization design study of low-Reynolds-number high-lift airfoils for the high-efficiency propeller of low-dynamic vehicles in stratosphere
cites work: Dynamics of laminar separation bubbles at low-Reynolds-number aerofoils
cites work: A review of particle swarm optimization. II: Hybridisation, combinatorial, multicriteria and constrained optimization, and indicative applications
cites work: A co-evolving framework for robust particle swarm optimization
cites work: Q5302586
cites work: An efficient adaptive forward-backward selection method for sparse polynomial chaos expansion
cites work: Influence of the transition of a laminar separation bubble on the downstream evolution of strong adverse pressure gradient turbulent boundary layers
description: scientific article; zbMATH DE number 7226147