Numerical simulation of internal and external inviscid and viscous 3D flow fields
Abstract
A numerical method for solving the 3D Euler equations in geometrical complex domains was developed. The approach divides the computational space into multiple blocks whose structure follows the natural lines of the conficuration. A systematic, multiblock grid generation scheme is used to produce the grid. The flow solutions are obtained by solving the Euler equations by a finite volume discretization and a RungeKutta time stepping scheme. The main advantage of this method is the applicability to complex geometries, for example complete aircraft configurations including wing, fuselage, canard and tail. The coupling with a 3D boundary layer method allows to account for viscous effects. Another application for the method was the simulation of flows in the presence of a propeller.
 Publication:

In AGARD Applications of Computational Fluid Dynamics in Aeronautics 27 p (SEE N8720199 1302
 Pub Date:
 November 1986
 Bibcode:
 1986acfd.agarQ....L
 Keywords:

 Computerized Simulation;
 Euler Equations Of Motion;
 Flow Distribution;
 Inviscid Flow;
 Three Dimensional Flow;
 Viscous Flow;
 Aircraft Configurations;
 Boundary Layer Equations;
 Computational Fluid Dynamics;
 Computational Grids;
 Finite Volume Method;
 Grid Generation (Mathematics);
 Projective Geometry;
 Propeller Slipstreams;
 RungeKutta Method;
 Three Dimensional Bodies;
 Fluid Mechanics and Heat Transfer