Numerical Study of the Lift Enhancement Mechanism of Circulation Control in Transonic Flow

The lift of an aircraft can be effectively enhanced by circulation control (CC) technology at subsonic speeds, but the efficiency at transonic speeds is greatly decreased. The underlying mechanism of this phenomenon is not fully understood. In this study, Reynolds averaged Navier—Stokes simulation w...

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Autores principales:	Ye Chen, Zhongxi Hou, Xiaolong Deng, Zheng Guo, Shuai Shao, Boting Xu
Formato:	article
Lenguaje:	EN
Publicado:	MDPI AG 2021
Materias:	circulation control effectiveness transonic flow flow control Motor vehicles. Aeronautics. Astronautics TL1-4050
Acceso en línea:	https://doaj.org/article/f8657444fb1f4edd9b43f813c834baa4
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spelling	oai:doaj.org-article:f8657444fb1f4edd9b43f813c834baa42021-11-25T15:57:03ZNumerical Study of the Lift Enhancement Mechanism of Circulation Control in Transonic Flow10.3390/aerospace81103112226-4310https://doaj.org/article/f8657444fb1f4edd9b43f813c834baa42021-10-01T00:00:00Zhttps://www.mdpi.com/2226-4310/8/11/311https://doaj.org/toc/2226-4310The lift of an aircraft can be effectively enhanced by circulation control (CC) technology at subsonic speeds, but the efficiency at transonic speeds is greatly decreased. The underlying mechanism of this phenomenon is not fully understood. In this study, Reynolds averaged Navier—Stokes simulation with <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><mi>k</mi><mo>−</mo><mi>ω</mi></mrow></semantics></math></inline-formula> shear stress transport model was utilized to investigate the mechanism of lift enhancement by CC in transonic flow. For validation, the numerical CC results were compared with the NASA experimental data obtained for transonic CC airfoil. Thereafter, the RAE2822 airfoil was modified with a Coanda surface. The lift enhancement effects of CC via steady blowing with different momentum coefficients were tested at <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><mi>M</mi><mi>a</mi><mo>=</mo><mn>0.3</mn></mrow></semantics></math></inline-formula> and 0.8 at <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><mi>α</mi><mo>=</mo><msup><mn>3</mn><mo>∘</mo></msup></mrow></semantics></math></inline-formula>, and various fluid mechanics phenomena were investigated. The results indicate that the flow structure of the CC jet is insensitive to the incoming flow conditions because of the similarity to the local static pressure field around the trailing edge of the airfoil. Owing to the appearance of shockwaves on the airfoil surface in the transonic regime, the performance of the CC jet is restricted to the trailing edge of the airfoil. Transonic CC achieved a slight improvement in aerodynamic performance owing to a favorable shift in the shockwave pattern and accelerated flow in the separation region on the airfoil surfaces. Revealing the mechanism of lift enhancement of CC in the transonic regime can facilitate the rational design of new fluidic actuators with high activity and expand the potential applications of CC technology.Ye ChenZhongxi HouXiaolong DengZheng GuoShuai ShaoBoting XuMDPI AGarticlecirculation controleffectivenesstransonic flowflow controlMotor vehicles. Aeronautics. AstronauticsTL1-4050ENAerospace, Vol 8, Iss 311, p 311 (2021)
institution	DOAJ
collection	DOAJ
language	EN
topic	circulation control effectiveness transonic flow flow control Motor vehicles. Aeronautics. Astronautics TL1-4050
spellingShingle	circulation control effectiveness transonic flow flow control Motor vehicles. Aeronautics. Astronautics TL1-4050 Ye Chen Zhongxi Hou Xiaolong Deng Zheng Guo Shuai Shao Boting Xu Numerical Study of the Lift Enhancement Mechanism of Circulation Control in Transonic Flow
description	The lift of an aircraft can be effectively enhanced by circulation control (CC) technology at subsonic speeds, but the efficiency at transonic speeds is greatly decreased. The underlying mechanism of this phenomenon is not fully understood. In this study, Reynolds averaged Navier—Stokes simulation with <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><mi>k</mi><mo>−</mo><mi>ω</mi></mrow></semantics></math></inline-formula> shear stress transport model was utilized to investigate the mechanism of lift enhancement by CC in transonic flow. For validation, the numerical CC results were compared with the NASA experimental data obtained for transonic CC airfoil. Thereafter, the RAE2822 airfoil was modified with a Coanda surface. The lift enhancement effects of CC via steady blowing with different momentum coefficients were tested at <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><mi>M</mi><mi>a</mi><mo>=</mo><mn>0.3</mn></mrow></semantics></math></inline-formula> and 0.8 at <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><mi>α</mi><mo>=</mo><msup><mn>3</mn><mo>∘</mo></msup></mrow></semantics></math></inline-formula>, and various fluid mechanics phenomena were investigated. The results indicate that the flow structure of the CC jet is insensitive to the incoming flow conditions because of the similarity to the local static pressure field around the trailing edge of the airfoil. Owing to the appearance of shockwaves on the airfoil surface in the transonic regime, the performance of the CC jet is restricted to the trailing edge of the airfoil. Transonic CC achieved a slight improvement in aerodynamic performance owing to a favorable shift in the shockwave pattern and accelerated flow in the separation region on the airfoil surfaces. Revealing the mechanism of lift enhancement of CC in the transonic regime can facilitate the rational design of new fluidic actuators with high activity and expand the potential applications of CC technology.
format	article
author	Ye Chen Zhongxi Hou Xiaolong Deng Zheng Guo Shuai Shao Boting Xu
author_facet	Ye Chen Zhongxi Hou Xiaolong Deng Zheng Guo Shuai Shao Boting Xu
author_sort	Ye Chen
title	Numerical Study of the Lift Enhancement Mechanism of Circulation Control in Transonic Flow
title_short	Numerical Study of the Lift Enhancement Mechanism of Circulation Control in Transonic Flow
title_full	Numerical Study of the Lift Enhancement Mechanism of Circulation Control in Transonic Flow
title_fullStr	Numerical Study of the Lift Enhancement Mechanism of Circulation Control in Transonic Flow
title_full_unstemmed	Numerical Study of the Lift Enhancement Mechanism of Circulation Control in Transonic Flow
title_sort	numerical study of the lift enhancement mechanism of circulation control in transonic flow
publisher	MDPI AG
publishDate	2021
url	https://doaj.org/article/f8657444fb1f4edd9b43f813c834baa4
work_keys_str_mv	AT yechen numericalstudyoftheliftenhancementmechanismofcirculationcontrolintransonicflow AT zhongxihou numericalstudyoftheliftenhancementmechanismofcirculationcontrolintransonicflow AT xiaolongdeng numericalstudyoftheliftenhancementmechanismofcirculationcontrolintransonicflow AT zhengguo numericalstudyoftheliftenhancementmechanismofcirculationcontrolintransonicflow AT shuaishao numericalstudyoftheliftenhancementmechanismofcirculationcontrolintransonicflow AT botingxu numericalstudyoftheliftenhancementmechanismofcirculationcontrolintransonicflow
_version_	1718413416044953600

Numerical Study of the Lift Enhancement Mechanism of Circulation Control in Transonic Flow

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