عنوان مقاله [English]
In this study, shock wave mitigation technique was analyzed using qualitative observations of plasma discharge in Mach 2.45 and atmospheric conditions testing. Plasma was produced in front of the aero-spike model by a 50 Hz, 50 mA, 30Kv electrical discharge and shadowgraph imaging technique at 300 frame per second and camera recording at 1000fps were used to record the qualitative results. Laboratory results show that increasing the magnetic field increases the frequency, stabilizes the glow discharge, changes the motion path of the charged particles from circular to cyclotron, improves plasma overlapping and also thickens the shock layer. Shadowgraph images at Mach 2.45 show that combining magnetism with and increased by 7.5 degrees at a shock wave angle and mitigates shock waves and removes the bow shock downstream of the spike. This is the most important result that indicates combining plasma and magnetism can remove shock waves at supersonic speeds and thus reduce wave drag.
 Yu Ch. Ganiev, V. P. Gordeev, A. V. Krasilnikov, V. I. Lagutin, V. N. Outmenikov, A. V. Panasenkov, Aerodynamic Drag Reduction by Plasma and Hot-Gas Injection, Journal of Thermophysics and Heat Transfer, January, Vol. 14, No.1 pp. 10-17, 1998.
 M. Mumivand, H. Mohammad Khani, Numerical study of aerodynamic drag reduction blunt nose with Spike and Jet injection combined axial and transverse, Journal of Mechanical Engineering modares, Vol. 16, No.7, pp. 133-142, 2016. (in Persian)
 J. S. Shang, Magneto- Aerodynamic Interaction in Weakly Ionized Hypersonic Flow, AIAA, Vol. 40, No.,pp.1170-77, 2002.
 A. Buseman, Elements of Aerodynamics of Supersonic Flow, The Macmillan Co., New York, pp.117-160, 1949.
 A. Kantrowitz, Flight Magnetohydrodynamics, pp. 221-232, Addison Wesley, 1960.
 D. Riggins, H. F. Nelson, E. Johnson, Blunt –Body Wave Drag Reduction Using Focused Energy Deposition, AIAA J., Vol. 37, pp. 460-464, 1996.
 E. D. Katzen, G. E. Kaattari, Inviscid Hypersonic Flow around Blunt Bodies, AIAA J., Vol. 3, pp. 1230-1237, 1965.
 R. Appartaim, E. D. Mezonlin, J. A. Johnson, Turbulence in Plasma-Induced Hypersonic Drag Reduction, AIAA J.,Vol. 40, 2002.
 V. P. Gordeev, A. V. Krasilnikov, V. I. Lagutin, V. N. Otmennikov, Plasma Technology for Reduction of Flying Vehicle Drag, Fluid Dynamics, pp. 312-313, 1996.
 R. J. Exton, B. Shirinzadeh, G. J. Brauckmann, G. C. Herring, W. C. Kelliher, On-Board Projection of a Microwave Plasma Upsteam of a Mach 6 Bow Shock Phys. Plasmas, Vol. 8, No. 11, pp. 5013-5017, 2001.
 A. S. Baryshnikov, I. V. Basargin, E. V. Dubinina, D. A. Fedotov, Rearrangement of The Shock Wave Structure in a Decaying Discharge Plasma, Tech. Phys. Lett., Vol. 23, No. 4, pp. 259-260, 1997.
 S. P. Kuo, I. M. Kalkhoran, D. Bivolaru, L. Orlick, Observation of Shock Wave Elimination by a Plasma in a M=2.5 Flow, Physics of Plasmas, Vol. 7, No. 5, pp. 1345-1348, 2000.
 S. P. Kuo, D. Bivolaru, Plasma Effect on Shock Waves in a Supersonic Flow, Physics of Plasmas, Vol. 9, No. 2, pp. 721-723, 2001.
 Chang K. Paul, Leading-Eadge Flow Seperation, ed., Pergamon, pp. 452-530, 1970.
 D. Bivolaru, S. P. Kuo, Aerodynamic Modification of Supersonic Flow around Truncated Cone Using Pulsed Electrical Discharges, AIAA J., Vol. 43, pp. 482-489, 2005.
 S. P. Kuo, Plasma Mitigation of Shock Wave: Experimental and Theory, Shock Waves, Vol. 17, pp. 225-239, 2007.
 S. P. Kuo, Air Plasma Mitigation of Shock Wave, Advances in Aerospace Science and Technology, Vol. 1, pp. 59-69, 2016.
 Equation, Table and Charts for Compressible Flow, 1953, http://naca.central.cranfield.ac.uk (accessed Dec 20, 2018).
 D. H. Michael, E. C. Rachel, M. Jaysen, K. Jayanta, A. Kareem, G.W. Jennifer, M. Calle, Revision of Paschen’s Law Relating to the ESD of Aerospace Vehicle Surfaces, 2017, https://ntrs.nasa.gov/search.jsp (accessed Dec 20, 2018).