Shock waves are presented in hypersonic aircrafts. They increase drag and as a result of additional friction, surface heating increases. In this research, a wind tunnel model; a combination of a 60o slender physical spike, used as cathode and a 60o truncated cone- cylinder, as anode, were experimented in flows with Mach numbers 1.5, 1.95, and 2.45. Plasma was produced in front of the aero-spike model by electrical discharge of 50 HZ, 30 KVDC, and 50 mA. Shadow and plasma glow imaging techniques were used simultaneously for flow and plasma visualization. Shadow imaging, in the afore mentioned Mach numbers, shows that the plasma being discharged behind shock wave, in spite of increasing the magnetic field, has a slight effect on decreasing the intensity of the shock wave. With increasing Mach number, the Shock wave of the truncated conical nose moves downstream and as a result of the plasma discharge taking place below the nose and the constant magnetic field, the wave below the nose is eliminated. The experimental results indicate that at Mach number 2.45, the shock wave attaches to the truncated nose, thus; the continuous plasma discharge below the spike and in front of the wave eliminates the wave. This is the most important result of this study indicates that aero-spike plasma discharge can remove shock waves and thus reduce drag.
Kuo, S.P., Kalkhoran, I.M., Bivolaru D., and Orlick L. “Observation of Shock Wave Elimination by a Plasma in a M 2.5 Flow”, Physics of Plasmas, Vol. 7, No.5, pp.1345-1348, 2005.
Kuo, S.P. and Bivolaru D. “Plasma Effect on Shock Waves in a Supersonic Flow”, Physics of Plasmas, Vol. 9, No. 2, pp.721-723, 2001.
Bivolaru, D. and Kuo, S.P. “Aerodynamic Modification of Supersonic Flow around Truncated Cone, Using Pulsed Electrical Discharges”, AIAA J., Vol. 43, pp. 1482-1489, 2005.
Kuo, S.P. “Plasma Mitigation of Shock Wave: Experimental and Theory”, Shock Waves, Vol. 17, No. 4, pp. 225-239, 2007.
Kuo, S.P. “Air Plasma Mitigation of Shock Wave”, Advances in Aerospace Science and Technology, Vol. 1, No. 2, pp.59-69, 2016.
Bivolaru, D. and Kuo, S.P. “Observation of Supersonic Shock Wave Elimination by a Plasma Aero- Spike”, Physics of Plasmas, Vol. 9, No. 2, pp. 721-723, 2002.
Mumivand, M. and Mohammad Khani, H. “Numerical Study of Aerodynamic Drag Reduction Blunt Nose with Spike and Jet Injection Combined Axial and Transverse”, Journal of Mechanical Engineering modares, Vol. 16, pp. 133-142, 2016 (In Persian).
khodayari, A., veisi, F., & rahimi, M. (2017). Experimental Study of Reducing the Intensity of Supersonic Shock Waves,
Using Continuous Plasma Discharge. Fluid Mechanics & Aerodynamics, 6(2), 61-70.
MLA
akram khodayari; farzad veisi; mahdi rahimi. "Experimental Study of Reducing the Intensity of Supersonic Shock Waves,
Using Continuous Plasma Discharge", Fluid Mechanics & Aerodynamics, 6, 2, 2017, 61-70.
HARVARD
khodayari, A., veisi, F., rahimi, M. (2017). 'Experimental Study of Reducing the Intensity of Supersonic Shock Waves,
Using Continuous Plasma Discharge', Fluid Mechanics & Aerodynamics, 6(2), pp. 61-70.
VANCOUVER
khodayari, A., veisi, F., rahimi, M. Experimental Study of Reducing the Intensity of Supersonic Shock Waves,
Using Continuous Plasma Discharge. Fluid Mechanics & Aerodynamics, 2017; 6(2): 61-70.
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