Numerical analysis and optimization of boundary layer suction on airfoils

Shi, Yayun; Bai, Junqiang; Hua, Jianmin; Yang, Tihao

doi:10.1016/j.cja.2015.02.011

Cited by 15 publications

(9 citation statements)

References 11 publications

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“…v s is the suction velocity, n is the number of suction holes, and d is the diameter of suction holes. So equation (6) can be written in the following form…”

Section: Effects Of Suction On the Laminar Separation And Transitionmentioning

confidence: 99%

“…1 The flight altitude of high altitude unmanned aircraft is generally more than 20 km, and the air density is low and kinematic viscosity coefficient is high in this height. So the aircraft flight environment belongs to low Reynolds number range (Reynolds number is less than l0 6 ). Under the condition of low Reynolds numbers, some special phenomena will occur in the aerodynamic characteristics of the aircraft.…”

Section: Introductionmentioning

confidence: 99%

“…1,4 NLF delays the transition by the positive pressure distribution. 5 HLFC is a blend of LFC and NLF, 6 and the combination of the surface modification and suction is the most used technology. 7 The suction flow control is one of the most mature and effective methods in many kinds of flow control methods.…”

Section: Introductionmentioning

confidence: 99%

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Research of the suction flow control on wings at low Reynolds numbers

Yang

et al. 2017

Proceedings of the Institution of Mechanical Engineers, Part G:

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Laminar separation and transition have significant effects on aerodynamic characteristics of the wing under the condition of low Reynolds numbers. Using the flow control methods to delay and eliminate laminar separation has great significance. This study uses the method combined with water tunnel test and numerical calculation to research the effects of suction flow control on the flow state and aerodynamic force of the wing at low Reynolds numbers. The effects of suction flow rate and suction location on laminar separation, transition and aerodynamic performance of the wing are further researched. The results of the research show that, the suction can control laminar separation and transition effectively, when the suction holes are in the interior of the separation bubble, and close to the separation point, the suction has the best control effect. When the Reynolds number is Re ¼ 3.0 Â 10 5 , the suction flow control can make the lift-to-drag ratio of the wing increase by 8.62%, and the aerodynamic characteristics of the wing are improved effectively.

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“…v s is the suction velocity, n is the number of suction holes, and d is the diameter of suction holes. So equation (6) can be written in the following form…”

Section: Effects Of Suction On the Laminar Separation And Transitionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Research of the suction flow control on wings at low Reynolds numbers

Yang

et al. 2017

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Therefore, the suction technique will have a broad application prospect in the future. So far the studies about suction mainly concentrate on the control of the boundary layer separation on the blade SS (Song et al 2006;Guo et al 2010;Shi et al 2015b) or the three-dimensional (3D) separation in the hub corner (Sachdeva et al 2011;Pönick et al 2013;Guo et al 2008;Marsan et al 2015). Apart from some researches about the effects of bleeding system on the compressor performance (Leishman et al 2007a(Leishman et al , 2007b(Leishman et al , 2007cGrimshaw et al 2015Grimshaw et al , 2016, there are only several investigations of suction technique on the control of TLF to improve the compressor performance and stability (Gümmer et al 2008;Dobrzynski et al 2008;Shi et al 2015a).…”

Section: Introductionmentioning

confidence: 99%

Control of Tip Leakage Flow in Axial Flow Compressor Cascade by Suction on the Blade Tip

Mao

Liu

Tang

2018

JAFM

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One of the important ways of improving axial compressor performance is to control the tip leakage flow near the endwall region. Numerical computations were conducted to investigate the impact of blade tip suction on the axial compressor cascade performance in current paper. Three suction schemes located on the blade tip with different chordwise coverage were investigated in total. The results show that the cascade overall performance can be effectively enhanced by the proper suction scheme on the blade tip and the best scheme should be arranged at slightly downstream of the onset point of the tip leakage vortex (TLV). The control effectiveness and mechanisms are different for the different suction schemes. For the suction scheme covering the starting point of TLV, the onset point of TLV is shifted downstream, while an additional induced leakage flow near the blade leading edge is generated resulting in the increase of mixing loss. It is more effective when the structure of the main TLV is destroyed and divided into different parts by applying the blade tip suction arranged slightly behind the onset point of TLV. In addition, the blade loading is redistributed near the blade tip after the blade tip suction and the total pressure loss caused by the suction slots should also be considered in the design process.

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“…The result shows the smaller blowing and larger suction velocity ratio gives the better result irrespective of the position of the hole. The suction controller with multi-holes shows better aerodynamic performance against the single hole [24]. Skarolek and Karabelas [25] used a non-conventional active flow control scheme that results in excellent efficiency in aerodynamic characteristics before and after the flow separation.…”

Section: Introductionmentioning

confidence: 99%

A Parametric Study on Control of Flow Separation Over an Airfoil in Incompressible Regime

Prabhu

Srinivas

2018

IIUMEJ

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This paper presents the effects of airfoil geometry on flow separation behavior and obtains the transition patterns at a specific angle of attack. A strong adverse pressure gradient field is observed at the leading edge of the airfoil, and it results in a flow detachment. Leading edge flow separation is studied along with the variation of skin friction coefficient over the airfoil. Novelty in the approach is the development of a hybrid control scheme to delay the flow separation with blowing/suction of air (termed active control) over the airfoil together with the tapping of flow from the pressure side as in a classical passive control procedure. The active controller delays the flow separation, while the passive controller is used to reduce the drag coefficient significantly and increases the total performance of an airfoil. The effectiveness of these controls is examined by varying the control parameters including blowing/suction velocity, the position of the slot in terms of percentage of chord and size of the slot. All the numerical simulations are carried out using ANSYS-Fluent software. A surrogate model is also developed to predict the aerodynamic characteristics conveniently without much computational effort. The outcome of this study reveals that the blowing/suction velocity has a higher influence in delaying the flow separation. ABSTRAK: Kertas ini membentangkan tentang kesan geometri aerofoil pada perubahan pemisah aliran udara dan memperoleh bentuk peralihan pada darjah yang tepat. Terdapat tekanan kuat yang tidak sesuai pada kawasan kecerunan di hujung hadapan permukaan aerofoil, dan ini menyebabkan aliran udara terpisah. Pemisah aliran udara pada hujung hadapan ini dikaji bersama koefisien geseran pada permukaan aerofoil. Pendekatan baru pada kaedah ini adalah berkaitan pembangunan skim kawalan hibrid bagi melengahkan aliran pemisah udara melalui tiupan/sedutan udara (kawalan aktif) ke atas aerofoil bersama ketukan pada aliran dari tepi tekanan seperti mana prosedur klasik kawalan pasif. Kawalan aktif ini melengahkan aliran pemisah udara, sebaliknya kawalan pasif telah digunakan bagi mengurangkan koefisien penangguhan dengan ketara dan menambahkan jumlah prestasi aerofoil. Keberhasilan kawalan-kawalan ini dikaji dengan mengubah parameter kawalan termasuk kelajuan tiupan/sedutan udara, posisi slot berdasarkan peratusan garis temu dan saiz slot. Semua simulasi-simulasi numerikal ini dijalankan menggunakan perisian Ansys-Fluent. Model pengganti turut dibangunkan untuk menjangka ciri-ciri aero-dinamik dengan mudah tanpa usaha pengiraan yang banyak. Keputusan kajian ini mendedahkan tentang kelajuan tiupan/sedutan udara berpengaruh besar dalam melambatkan pemisahan aliran udara.

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Numerical analysis and optimization of boundary layer suction on airfoils

Cited by 15 publications

References 11 publications

Research of the suction flow control on wings at low Reynolds numbers

Research of the suction flow control on wings at low Reynolds numbers

Control of Tip Leakage Flow in Axial Flow Compressor Cascade by Suction on the Blade Tip

A Parametric Study on Control of Flow Separation Over an Airfoil in Incompressible Regime

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