等离子体气动激励控制超声速边界层分离的实验研究

doi:10.7527/S1000-6893.2014.0062

Abstract

Abstract:

Plasma aerodynamic actuation and supersonic flow interaction has become the focus of researches. There is a wide range of universal phenomenon of shock wave and boundary layer interaction in supersonic aircraft. Experimental investigation on boundary layer separation induced by ramp and impinging shock wave are performing in supersonic flow by plasma aerodynamic actuation. Through schlieren imaging and wall static pressure results, plasma-shock wave interaction and shock-boundary layer interaction mechanism are studied. Experimental results show that the millisecond plasma actuation can make the shock wave induced by the ramp forward and enlarge the separation area. At the same time, the intensity of shock wave induced by the ramp is weakened. The main control mechanism are Joule heating effect. The microsecond plasma actuation can control the boundary layer separation induced by the impinging shock wave and reduce the separation area but the overall pressure reduced. The main control mechanism is Joule heating effect and impact effect based on experimental results.

Key words: supersonic, shock wave, boundary layer, plasma, flow control

CLC Number:

V232

SUN Quan, CUI Wei, CHENG Bangqin, JIN Di, LI Jun. Experimental investigation on supersonic boundary layer separation control by plasma aerodynamic actuation[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(2): 501-509.

References

[1] Roth J R. Aerodynamic flow acceleration using paraelectric and peristaltic electrohydrodynamic effects of a one atmosphere uniform glow discharge plasma[J]. Physics of Plasmas, 2003, 10(5): 2117-2126.

[2] Enloe C L, McLaughlin T E, van Dyken R D, et al. Mechanisms and responses of a single dielectric barrier plasma actuator: plasma morphology[J]. AIAA Journal, 2004, 42(3): 589-594.

[3] Sasoh A, Kikuchi K, Sakai T. Spatio-temporal filament behaviour in a dielectric barrier discharge plasma actuator[J]. Journal of Physics D: Applied Physics, 2007, 40(14): 4181-4184.

[4] Porter C O, Baughn J W, McLaughlin T E, et al. Plasma actuator force measurements[J]. AIAA Journal, 2007, 45(7): 1562-1570.

[5] Post M L, Corke T C. Separation control using plasma actuators: dynamic stall vortex control on oscillating airfoil[J]. AIAA Journal, 2006, 44(12): 3125-3135.

[6] Webb N, Clifford C, Samimy M. An investigation of the control mechanism of plasma actuators in a shock wave-boundary layer interaction, AIAA-2013-0402[R]. Reston: AIAA, 2013.

[7] Webb N, Clifford C, Samimy M. Control of oblique shock wave-boundary layer interactions using plasma actuators, AIAA-2012-2810[R]. Reston: AIAA, 2012.

[8] Webb N, Clifford C, Samimy M. Preliminary results on shock wave/boundary layer interaction control using localized arc filament plasma actuators, AIAA-2011-3426[R]. Reston: AIAA, 2011.

[9] Nishihara M, Gaitonde D, Adamovich I V, et al. Effect of nanosecond pulse discharges on oblique shock and shock wave-boundary layer interaction, AIAA-2013-0416[R]. Reston: AIAA, 2013.

[10] Narayanaswamy V, Raja L L, Clemens N T. Control of unsteadiness of a shock wave/turbulent boundary layer interaction by using a pulsed-plasma-jet actuator[J]. Physics of Fluids, 2012, 24(1): 076101.

[11] Kalra C S, Zaidi S, Miles R B. Shock wave induced turbulent boundary layer separation control with plasma actuators, AIAA-2009-1002[R]. Reston: AIAA, 2009.

[12] Sun Q, Cheng B Q, Li Y H, et al. Experimental inves-tigation on hypersonic flow and plasma aerodynamic actuation interaction[J]. Plasma Science and Technology, 2013, 15(9): 908-915.

[13] Sun Q, Cheng B Q, Li Y H, et al. Computational and experimental analysis of Mach 2 air flow over a blunt body with plasma aerodynamic actuation[J]. Science China Technological Sciences, 2013, 56(2): 795-801.

[14] Wang J, Li Y H, Xing F. Investigation on oblique shock wave control by arc discharge plasma in supersonic airflow[J]. Journal of Applied Physics, 2009, 106(7): 073307.

[15] Su C B, Li Y H, Cheng B Q. Experimental investigation of MHD flow control for the oblique shock wave around the ramp in low-temperature supersonic flow[J]. Chinese Journal of Aeronautics, 2010, 23(1): 22-32.

[16] Leonov S B. Study of a structural plasma influence on characteristics of viscous friction and separated near-surface zone position under high-speed airflow, ADA 433384[R]. 2005.

Experimental investigation on supersonic boundary layer separation control by plasma aerodynamic actuation

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