Computational methods for vortex dominated compressible flows
Abstract
The principal objectives were to: understand the mechanisms by which Euler equation computations model leading edge vortex flows; understand the vortical and shock wave structures that may exist for different wing shapes, angles of incidence, and Mach numbers; and compare calculations with experiments in order to ascertain the limitations and advantages of Euler equation models. The initial approach utilized the cell centered finite volume Jameson scheme. The final calculation utilized a cell vertex finite volume method on an unstructured grid. Both methods used RungeKutta four stage schemes for integrating the equations. The principal findings are briefly summarized.
 Publication:

Massachusetts Inst. of Tech. Report
 Pub Date:
 August 1987
 Bibcode:
 1987mit..reptY....M
 Keywords:

 Computational Fluid Dynamics;
 Computational Grids;
 Euler Equations Of Motion;
 Shock Waves;
 Vortices;
 RungeKutta Method;
 Aerodynamic Configurations;
 Delta Wings;
 Finite Volume Method;
 Leading Edges;
 Mach Number;
 Fluid Mechanics and Heat Transfer