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    ABSTRACT: This paper presents the numerical investigation of supersonic flow through a De Lavai nozzle by time marching technique. This approach utilizes a Lax-Wendroff finite difference solution of the governing unsteady Euler equations. Starting from arbitrarily assumed initial conditions, the steady state solution for the flow field, shock wave shape and location is achieved asymptotically. The result obtained by Lax-Wendroff method is compared with CFX software. The rcsults are analyzed by studying the shape of the shock wave, the shock standoff distance and the flow parameters in the flow field at steady state. It is observed that the shock standoff distance is not influenced by the variation in total pressure but it depends on upstream Mach numbers. The properties along the centerline that are obtained from the computation are also compared and found to be in good agreement with the simple one-dimensional isentropic solution.
    No preview · Article · Jan 2006 · International Journal of Turbo and Jet Engines