Effect of jet width and momentum coefficient of active control over NACA0012 airfoil using synthetic jet

Effect of jet width and momentum coefficient of active control over NACA0012 airfoil using synthetic jet

Mohamed C. SaadiLakhdar Bahi 

Department of Physic, Laboratory of Physic Energetic, Fréres Mentouri Constantine1 University, Constantine, Algeria

Corresponding Author Email: 
18 January 2018
| |
13 September 2018
| | Citation



In this study, the effect of the jet control width and its momentum coefficient on the flow over a NACA0012 airfoil is investigated numerically for a Reynolds number equal to 2.88x106. The jet is placed at 15% of the chord length from the leading edge on the upper surface of the airfoil. The calculation was carried out using the solver URANS with the (k-ε) RNG model. Simulation results for an incompressible fully turbulent flow, varying the jet width from 0.5 to 3.5 percent of the chord length with jet control angle β equal to 450, the lift to drag ratio increase. However, an optimum jet width of 2% of the profile chord, leads to better performance. I is also be observed, when the momentum coefficient rises, the lift coefficient increases reaching about 86% improvement (for better improvement by 85.93%) and the stall angle is delayed from 160 to 220. This parametric study led to select the control parameters for the best aerodynamic performance of the airfoil.


control, flow separation, synthetic jet, NACA0012 profile

1. Introduction
2. Numerical Simulation
3. Validating Results
4. Results and Discussion
5. Conclusions

[1] Wygnanski IJ. (1997). Boundary layer and flow control by periodic addition of momentum. AIAA 97-2117.

[2] Greenblatt D, Wygnanski IJ. (2000). Control of flow separation by periodic excitation. Progress in Aerospace Sciences 36(7): 487-545. https://doi.org/10.1016/S0376-0421(00)00008-7

[3] Corke T. (2002). Design of aircraft, Prentice-Hall, New York.

[4] Gillero P. (2011). Analytical models for the limiting condition of a pulsed jet control. 20th French Congress of Mechanics, Besançon, August 29th to September 2nd, 2011. 

[5] Modi VJ, Hill SS, Yokomizo T. (1995). Drag reduction of trucks through boundary-layer control. Journal of Wind Engineering and Industrial Aerodynamics 54(3): 583-594. https://doi.org/10.1016/0167-6105(94)00074-n

[6] Jirasek A. (2004). A vortex generator model and its application to flow control. AIAA 2004-4965.

[7] Wygnanski IJ. (2004). The variables affecting the control of separation by periodic excitation. AIAA 2004-2505.

[8] Yousefi K Saleh R. (2014). The effects of trailing edge blowing on aerodynamic characteristics of the NACA0012 airfoil and optimization of the blowing slot geometry. Journal of Theoretical and Applied Mechanics 52(1): 165-179.

[9] Collins FC. (1979). Boundary layer control on wings using sound and leading edge serration. AIAA 1979-1875. 

[10] Chang PK. (1976). Control of flow separation, hemisphere. Washington, DC.

[11] Gad-el-Hak M. (2000). Flow control, passive, active and reactive management. Cambridge Univ. Press, Cambridge, UK.

[12] Tuck A, Soria AJ. (2004). Active flow control over NACA 0015 airfoil using ZNMF jet. 15th Australasian Fluid Mechanics Conference. 

[13] Zaman KBMQ, Bar-Sever A, Mangalam SM. (1987). Effect of acoustic excitation on the flow over a low-Re airfoil. Journal of Fluid Mechanics 182(1): 127-148. https://doi.org/10.1017/s0022112087002271

[14] Tang H, Salunkhe P, Zheng YY, Du JX, Wu YH. (2004). On the use of synthetic jet actuator arrays for active flow separation control. Experimental Thermal and Fluid Science 57(2004): 1-10.

[15] McCormick DC. (2000). Boundary layer separation control with directed synthetic jets. AIAA 2000-0519.

[16] Rizzeta DP, Visbal MR, Stank MJ. (1999). Numerical investigation of synthetic jet flow fields. AIAA Journal 37: 919-927.

[17] Wu JZ, Lu XY, Denny AG, Fan M, Wu JM. (1998). Post-Stall flow control on an airfoil by local unsteady forcing. Journal of fluid Mechanics 371: 21-58.

[18] Nae C. (1998). Synthetics jets influence on NACA0012 airfoil at high angle of attacks. AIAA papers 98.

[19] Rosas CR. (2005). Numerical simulation of flow separation control by oscillator fluid injection. Doctor of Philosophy Thesis, A&M University, Texas.

[20] Esmaeili H, Tadjfar M, Bakhtian A. (2014). Tangential synthetic jets for separation control. Journal of fluids and structures 45: 50-65.

[21] Donovan JF, Kral LD, Cary AW. (1998). Active flow control applied to an airfoil. AIAA Paper 98-0210.

[22] Piperas AT. (2010). Investigation of boundary layer suction on a wind turbine airfoil using CFD. Master thesis. Technical University of Denmark.

[23] You D, Moin P. (2008). Active control of flow separation over an airfoil using synthetic. Journal of Fluids and Structures 24: 1349-1357.

[24] Akcayoz E Tuncer IH. (2009). Numerical investigation of flow control over an airfoil using synthetic jets and its optimization. International Aerospace Conference, Turkey. 

[25] Montazer E, Mirzaei M, Salami E, Ward TA, Romli FI, Kazi SN. (2016). Optimization of a synthetic jet actuator for flow control around an airfoil. IOP Conference series: Materials Science and Engineering 152(2016): 012023. https://doi.org/10.1088/1757-899X/1/012007

[26] Boukenkoul MA, Li FC, Aounallah M. (2017). A 2D simulation of the flow separation control over a NACA0015 airfoil using a synthetic jet actuator. IOP Conference Series: Materials Science and Engineering 187(2017): 012007. https://doi.org/10.1088/1757-899x/1/012007

[27] Abed KN, Azzawi IDJ. (2015). Control of flow separation over NACA0015 airfoil using synthetic jet actuators. Diyala Journal of Engineering Sciences 674-685.

[28] Crook A, Wood NJ. (2001). Measurements and  Visualizations of synthetic jets. AIAA Paper 2001-0145. 

[29] Glezer, Amitay M. (2002). Synthetic Jets. Annu. Rev. Fluid Mech 34: 503-529.

[30] Smith BL, Glezer A. (1997). Victoring and small-scalemotions effected in free shear flows using synthetic jet actuators. AIAA 35th Aerosp. Sci. Meet 97-0213.

[31] Smith BL, Glezer A. (1999). Victoring of a high  ratio rectangular air jet using a zero net-mass- flux control jet. Bul, Am Phys Soc 39: 1894. 

[32] Yousefi MK, Salah R. (2014). The effect of trailing edge blowing on aerodynamic characteristics of the NACA0012 airfoil and optimization of the blowing slot geometry. Journal of Theoretical and Applied Mechanics Warsaw 165-179.

[33] Gregory N, Reilly CLO. (1973). Low-speed Aerodynamic Characteristics of  NACA0012 Aerofoil section, including the effects of upper-surface roughness simulating hoar frost. Aerodynamics division N.P.L. Aeronautical Research Council. London. 

[34] Luo DH, Sun XJ, Huang DG, Wu GQ. (2011). Flow control effectiveness of synthetic jet. Stalled Airfoil March 225 Part C: 2106-2114. https://doi.org/10.1177/0954406211407255