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Theoretical study of plasma effect on a conical shock wave
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View: Figures


Image of FIG. 1.
FIG. 1.

(Color online) (a) Superimposed shadowgraph showing the baseline shock front and a shock front modified by the plasma; the Mach 2.5 flow is from left to right. As shown both shock fronts are attached to the tip of the cone model; the plasma modified shock front is located upstream from the baseline and has a larger shock angle. (b) A photo of the cone model.

Image of FIG. 2.
FIG. 2.

Geometry for the numerical solution of deflected flow over a cone.

Image of FIG. 3.
FIG. 3.

(Color online) (a) , the deflection angle, and (b) , the Mach number, of an incoming flow after being scattered by a plasma spike having the peak density with varying from 0.77 to 0.9; , a normalized radial coordinate; is the effective length of the plasma spike.

Image of FIG. 4.
FIG. 4.

(Color online) Attached shocks in a supersonic flow (Mach 2.5 before being deflected by the plasma spike) over a cone (represented by the shadow region) for two cases, and (i.e., plasma density , no discharge, and , corresponding to an intense discharge), where the normalized coordinates and . The line labeled (no discharge) represents the baseline conic shock front having a constant shock angle .


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752b84549af89a08dbdd7fdb8b9568b5 journal.articlezxybnytfddd
Scitation: Theoretical study of plasma effect on a conical shock wave