Accession Number : ADA135855

Title :   Implicit Numerical Solution for a Normal Shock.

Descriptive Note : Master's thesis,

Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING

Personal Author(s) : Allen,C M

PDF Url : ADA135855

Report Date : May 1983

Pagination or Media Count : 93

Abstract : There are basically two techniques used to solve the Navier-Stokes equations for fluid flow. These techniques are implicit and explicit methods. Both methods along with characteristic boundary conditions for solving quasi-one-dimensional nozzle flow are presented. Two types of characteristic boundary conditions, those of Steger and McKenna, were tested for each scheme. Solutions of isentropic supersonic flow and flow with shocks were obtained for a diverging nozzle. The behavior of each boundary condition on both implicit and explicit schemes were the same. They deviated from the theoretical values by less than one percent. A test to determine the utility of each scheme was run by allowing the exit boundary conditions to change in the hope of forcing the shock to move upstream or downstream. The shock would not move in the implicit scheme for either boundary condition. The explicit scheme could move the shock, but only when Steger's boundary condition was used. (This is the one which specified only pressure.) (Author)

Descriptors :   *Flow fields, *Shock waves, Navier stokes equations, Boundary value problems, Mathematical prediction, Numerical analysis, Partial differential equations

Subject Categories : Numerical Mathematics
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE