Inviscid flow over a supersonic cone-cylinder with thermal plasma filaments projecting upstream of its nose is analyzed numerically. The plasma filaments are idealized as concentric annular layer heat sources. Two limiting cases are assumed. These are, respectively, gas pressure p and gas density rho constant inside the layers during their formation. For the first case, the drag reduction energetic efficiency remains less than unity for Mach numbers M = 1.7-7 for an assumed layer configuration. In the second, the efficiency becomes greater than unity for M = 2.5 and reaches its maximum value at M = 5 for an optimal layer arrangement. This configuration consists of one central filament and another layer projecting from the cone surface at a radial distance from the cone axis of symmetry one-third of the cylinder radius.
Drag reduction by plasma filaments over supersonic forebodies
Reduzierung des Strömungswiderstandes supersonisch umströmter Körper mit Plasmafäden
AIAA Journal ; 41 , 12 ; 2403-2409
2003
7 Seiten, 11 Bilder, 14 Quellen
Article (Journal)
English
FLUID DYNAMICS - Drag Reduction by Plasma Filaments over Supersonic Forebodies
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