Appearance of Midair plasma extenuation of Shock Wave

International Journal of Applied Physics

© 2016 by SSRG - IJAP Journal

Volume 3 Issue 1

Year of Publication : 2016

Authors : G.Harikrishnan, Seethalakshmi.S

10.14445/23500301/IJAP-V3I2P104

How to Cite?

G.Harikrishnan, Seethalakshmi.S, "Appearance of Midair plasma extenuation of Shock Wave," SSRG International Journal of Applied Physics, vol. 3,  no. 1, pp. 18-22, 2016. Crossref, https://doi.org/10.14445/23500301/IJAP-V3I2P104

Abstract:

Shock wave is a detriment in the growth of supersonic aircrafts; it risesflow drag as well as external heating from extra friction; it similarly initiates sonicboom on the ground which prevents supersonic jetliner to fly overland. A shockwave extenuationmethod is established by experiments directed in a Mach 2.5wind tunnel. Non-thermal air plasma produced symmetrically in obverse of a windtunnel perfect and upstream of the shock, by on-board 60 Hz episodic electric a discharge, works as a plasma deflector, it bouncesreceived flow to alter theshock from a well-defined involved shock into aextremely curved shock structure. In asequence with growing discharge intensity, the altered curve shock growthsshock angle and changes upstream to become separate with growing standoff distancefrom the model. It develops diffusive and evaporates near the top of the discharge.The flow deflection growths the equivalent cone angle of the model, whichin essence, decreases the corresponding Mach number of the received flow, establishingthe discount of the shock wave drag on the cone. When this corresponding cone angleexceeds a dangerous angle, the shock develops detached and fades away. This shockwave mitigation method helps drag discount as well as removes sonic boom.

Keywords:

Shock Wave Mitigation, Electric Discharge, Air Plasma Deflector, Shadowgraph,Drag Reduction, Wind Tunnel, Charge Transfer

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