ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Experimental study of controlling flat transition using surface dielectric barrier discharge actuator
Received date: 2015-03-26
Revised date: 2015-09-16
Online published: 2015-09-30
Supported by
National Basic Research Program of China:Mechanism and Method for Drag Reduction of Trunk Liner (2014CB744800);NUAA Fundamental Research Funds (NS2013013);Fundamental Research Funds for the Central Universities (NP2014602);Aeronautical Science Foundation of China (2013ZA52009)
In a low speed jet wind tunnel, the transition point of a flat plate controlled by a single-stage dielectric barrier discharge (DBD) plasma actuator has been studied. Applying hot wire measurement technology, the transition location is judged by boundary layer velocity fluctuation and velocity profile. The flow speed of the experiments is 15m/s and the discharge parameters of the actuator are voltage peak to peak value is 11 kV, frequency is 4.7 kHz. After the analysis of the velocity fluctuation of the same height within boundary layer, the results show that the transition point is delayed about 40 mm farther downstream when the actuator is working. With the same flow speed and actuator distribution, actuators with different discharge parameters and their effects on the velocity profile, velocity fluctuation and amplitude spectrum of hot-wire signal within the boundary layer have been studied. It is discovered that higher discharge voltage,frequency and duty ratio can further delay the transition point. According to the experiment results, the jet generated by the plasma actuator strengthens the fluid stability of the boundary layer. As the discharge voltage, frequency and duty ratio goes up, the power of the jet gets stronger, which further strengthens the boundary layer stability and delays the transition location.
LU Jichun , SHI Zhiwei , DU Hai , HU Liang , LI Zheng , SONG Tianwei . Experimental study of controlling flat transition using surface dielectric barrier discharge actuator[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016 , 37(4) : 1166 -1173 . DOI: 10.7527/S1000-6893.2015.0256
[1] WRIGHT M C M, NELSON P A. Wind tunnel experiments on the optimization of distributed suction for laminar flow control[J]. Proceedings of the Institution of Mechanical Engineers, 2001, 215(6):343.
[2] ZAMAN K B. Effect of acoustic exciation on the flow over a low-Re airfoil[J]. Journal of Fluid Mechanics, 1987, 182(4):127-148.
[3] ARGA S P S. Buoyancy effects in a horizontal flat-plate boundary layer[J]. Journal of Fluid Mechanics, 1975, 68(2):321-343.
[4] MALIK M R.Ion wind drag reduction[C]//21st Aerospace Sciences Meeting. Reston:AIAA, 1983:203-208.
[5] ROTH J R.Interaction of electromagentic fields with magnetized plasmas[R]. Tennessee:Tennessee University, 1994.
[6] ROTH J R.Investigation of a uniform glow discharge plasma in atmospheric air[R]. Tennessee:Tennessee University, 1994.
[7] ROTH J R,Sherman D M.Boundary layer flow control with a one atmosphere uniform glow discharge surface plasma[C]//36th AIAA Aerospace Science Meeting including the New Horizons Forum and Aerospace Exposition. Reston:AIAA, 1997:113-119.
[8] GRUNDMANN S, CAMERON T. Experimental transition delay using glow-discharge plasma actuators[J]. Experiments in Fluids, 2007, 42(4):653-657.
[9] GRUNDMANN S, TROPEA C. Active cancellation of artificially introduced Tollmien-Schlichting waves using plasma actuators[J]. Experiments in Fluids, 2008, 44(5):795-806.
[10] DUCHMANN A, SIMON B, MAGIN P, et al. In-flight transition delay with DBD plasma actuators[C]//51st AIAA Aerospace Science Meeting including the New Horizons Forum and Aerospace Exposition. Reston:AIAA, 2013:103-114.
[11] HANSON R E, LAVOIE P, BADE K M,et al.Steady-state closed-loop control of bypass boundary layer transition using plasma actuators[C]//50st AIAA Aerospace Science Meeting including the New Horizons Forum and Aerospace Exposition. Reston:AIAA, 2012:82-95.
[12] BELSON B A, MEIDELL K, HANSON R,et al.Comparison of plasma actuators in simulations and experiments for control of bypass transition[C]//50th AIAA Aerospace Science Meeting including the New Horizons Forum and Aerospace Exposition. Reston:AIAA, 2012:101-109.
[13] 史志伟, 范本根. 不同结构等离子体激励器流场特性实验研究[J]. 航空学报, 2011, 32(9):1583-1589. SHI Z W, FAN B G. Experimental study on flow field characteristics of different plasma actuators[J]. Acta Aeronautica et Astronautica Sinica, 2011, 32(9):1583-1589(in Chinese).
[14] 杜海, 史志伟. 等离子体激励器对微型飞行器横航向气动力矩控制的实验研究[J]. 航空学报, 2012, 32(10):1781-1790. DU H, SHI Z W. Experimental study of directional-lateral aerodynamic moment control of micro air vehicle by plasma actuators[J]. Acta Aeronautica et Astronautica Sinca, 2012, 32(10):1781-1790(in Chinese).
[15] 杜海. 等离子体流动控制技术及其在飞行器上的应用研究[D]. 南京:南京航空航天大学, 2012. DU H. Plasma flow control technology and its application on flight vehicle[D]. Nanjing:Nanjing University of Aeronautics and Astronautics, 2012(in Chinese).
/
| 〈 |
|
〉 |
CJA