A PANSONIC NavierStokes solver
Abstract
A finitedifference formulation of the full NavierStokes equations which demonstrates a capability to economically solve twodimensional problems has been developed. The basic algorithm was derived from the full, Reynoldsaveraged, conservative, NavierStokes equations expressed in curvilinear coordinates. Eddy viscosity was determined by the Baldwin and Lomax algebraic turbulence model. This noniterative, secondorder accurate, implicit, numerical algorithm is based on the approximate factorization finitedifference scheme of Beam and Warming. Results indicate a facility for solving subsonic, transonic, and supersonic (hence PANSONIC) flows about arbitrary airfoils for a wide range of Reynolds numbers, Mach numbers, and angles of attack. Current computations demonstrate that vectorized implementations of this algorithm can solve steadystate, twodimensional problems in five to ten minutes of computer time.
 Publication:

14th Fluid and Plasma Dynamics Conference
 Pub Date:
 June 1981
 Bibcode:
 1981fpdy.confQ....C
 Keywords:

 Airfoil Profiles;
 Finite Difference Theory;
 NavierStokes Equation;
 Subsonic Flow;
 Supersonic Flow;
 Transonic Flow;
 Algorithms;
 Angle Of Attack;
 Computer Techniques;
 Eddy Viscosity;
 Equilibrium Flow;
 Mach Number;
 Reynolds Number;
 Spherical Coordinates;
 Turbulence Models;
 Two Dimensional Flow;
 Fluid Mechanics and Heat Transfer