Parametric study on wing-lambda-shock formation

CORC > 力学研究所 > 中国科学院力学研究所 > 流固耦合系统力学重点实验室(2012-)

	Parametric study on wing-lambda-shock formation
	Chainok S ; Rungroch T ; Chairach P ; Prapamonthon P ; Yooyen S ; Yin B(银波); Yang GW(杨国伟); Ju SJ(鞠胜军)
	2021
会议日期	10 August 2021 到 12 August 2021
会议地点	Virtual, Online
关键词	Shock Supersonic flow Transonic flow
页码	V001T02A001
英文摘要	It is well-known that a wing is one of the most important parts of an aircraft as it is used to generate lift force. According to a wing moving at sufficiently high subsonic speeds, the flow speed on the wing's upper surface can be supersonic due to acceleration through the curvature-created suction, thereby forming a shock wave in a lambda shape. Additionally, the lambda shock can interact with the boundary layer flow. These phenomena relate to disturbances in the flow field, including flow separation, thus causing undesirable effects on lift production. Hence, a better understanding of the phenomenon of wing-lambda-shock formation and its nature is essential. This study presents a numerical investigation of the lambda-shock formation on an ONERA M6 wing, which is known as a swept, semi-span wing with no twist, under parametric effects of angleof-attack, and free-stream Mach number, which is increased up to the supersonic regime. The pressure coefficients obtained by simulations are validated by open data. Then, numerical results in terms of the local pressure coefficient, local Mach number, averaged lift and drag coefficients, and?-shape characteristics based on Mach number and pressure coefficients are discussed under an investigated range of the parameters. Results show that the angle-of-attack and free-stream Mach number can affect the lambda shock formation on the wing upper surface physically. Specifically, an iso-sonic surface with lambda shock waves is disturbed when the angle-of-attack and free-stream Mach number vary in an investigated range. This also affects lift and drag coefficients of the wing. © 2021 by ASME.
会议录	American Society of Mechanical Engineers, Fluids Engineering Division (Publication) FEDSM
语种	英语
URL标识	查看原文
内容类型	会议论文
源URL	[http://dspace.imech.ac.cn/handle/311007/87795]
专题	力学研究所_流固耦合系统力学重点实验室(2012-)
作者单位	1.Key Laboratory for Mechanics in Fluid Solid Coupling Systems, Institute of Mechanics, Chinese Academy of Sciences, Beijing, 100190, China 2.Key Laboratory for Computational Mechanics and Heat Transfer Applications, Department of Aeronautical Engineering, International Academy of Aviation Industry, King Mongkut's Institute of Technology Ladkrabang, Bangkok, 10520, Thailand
推荐引用方式 GB/T 7714	Chainok S,Rungroch T,Chairach P,et al. Parametric study on wing-lambda-shock formation[C]. 见:. Virtual, Online. 10 August 2021 到 12 August 2021.