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.


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    Title :

    Drag reduction by plasma filaments over supersonic forebodies


    Additional title:

    Reduzierung des Strömungswiderstandes supersonisch umströmter Körper mit Plasmafäden


    Contributors:

    Published in:

    AIAA Journal ; 41 , 12 ; 2403-2409


    Publication date :

    2003


    Size :

    7 Seiten, 11 Bilder, 14 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




    Drag Reduction by Plasma Filaments over Supersonic Forebodies

    V. R. Soloviev / V. M. Krivtsov / A. M. Konchakov et al. | AIAA | 2003