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

Abstract

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 = 3.0 × 10⁵, 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.

Keywords

Flow control suction low Reynolds number water tunnel test numerical calculation

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References

Aaron AT, William SS and Helen LR. Laminar flow control flight experiment design and execution. In: 52nd Aerospace sciences meeting, National Harbor, MD, 13–17 January 2014.

Selig MS, Guglielmo JJ, Broern AP, et al. Experiments on airfoils at low Reynolds numbers. In: Aerospace sciences meeting and exhibit, Reno, NV, 15–18 January 1996. AIAA.

Kral LD. Active flow control technology. ASME FED, Technical Brief 2000: 1–28.

Chen

Seele

Wygnanski

. Flow control on a thick airfoil using suction compared to blowing. AIAA J 2013; 51: 1462–1472.

Poll D. Laminar flow control for aircraft - Lessons from the past and prospects for the future. In: Fluids 2000 Conference and Exhibit, Denver, CO., 19–22 June 2000. AIAA.

Shi

Bai

Hua

et al.

Numerical analysis and optimization of boundary layer suction on airfoils. Chin J Aeronaut 2015; 28: 357–367.

Yong-Sun W, Collier F, Richard W, et al. Design of a hybrid laminar flow control nacelle. In: 30th Aerospace Sciences Meeting & Exhibit, Reno, NV, 6–9 January 1992. AIAA.

Erich S. experimental investigation of laminar flow control on a supersonic swept wing by suction. In: 4th Flow control conference, Seattle, Washington, 23–26 June 2008.

Redha W and David B. Suction effects on the transition and reattachment of a transitional bubble. In: 51st AIAA aerospace sciences meeting, Grapevine (Dallas/Ft. Worth Region), TX, 7–10 January 2013.

10.

Packard

Thake

Bonilla

et al.

Active control of flow separation on a laminar airfoil. AIAA J 2008; 51: 1032–1041.

11.

Wright

MCM

Nelson

. Wind tunnel experiments on the optimization of distributed suction for laminar flow control. J Aerospace Eng 2001; 215: 343–354.

12.

Chng

Rachman

Tsai

et al.

Flow control of an airfoil via injection and suction. J Aircraft 2009; 46: 291–300.

13.

Oyewola

Djenidi

Antonia

. Combined influence of the Reynolds number and localised wall suction on a turbulent boundary layer. Exp Fluids 2003; 35: 199–206.

14.

Joseph

Amandolese

Edouard

et al.

Flow control using MEMS pulsed micro-jets on the Ahmed body. Exp Fluids 2013; 54: 1–12.

15.

Bryan M and Michael S. Surface oil flow measurements on several airfoils at low Reynolds numbers. In: 21st AIAA applied aerodynamics conference, Orlando, FL, 23–26 June 2003.

16.

Dongli

Yanping

Yuhang

et al.

Effects of relative thickness on aerodynamic characteristics of airfoil at a low Reynolds number. Chin J Aeronaut 2015; 28: 1003–1015.

17.

Robin L and Florian M. Transition modeling for general CFD applications in aeronautics. In: 43rd AIAA aerospace sciences meeting and exhibit, Reno, NV, 10–13 January 2005.

18.

Menter

. Two-equation eddy-viscosity turbulence models for engineering applications. AIAA J 1994; 32: 1598–1605.

19.

Robert JM, Betty SW and Betty FM. Experimental results for the Eppler 387 airfoil at low Reynolds numbers in the Langley low-turbulence pressure tunnel. Washington, D.C: NASA Langley Research Center, 1988. Report no. NASA-TM-4062.

20.

Redha W and David B. Effects of distributed suction on an airfoil at low Reynolds number. In: 40th Fluid dynamics conference and exhibit, Chicago, IL, 28 June–1 July 2010.