A PANSONIC Navier-Stokes solver
Abstract
A finite-difference formulation of the full Navier-Stokes equations which demonstrates a capability to economically solve two-dimensional problems has been developed. The basic algorithm was derived from the full, Reynolds-averaged, conservative, Navier-Stokes equations expressed in curvilinear coordinates. Eddy viscosity was determined by the Baldwin and Lomax algebraic turbulence model. This non-iterative, second-order accurate, implicit, numerical algorithm is based on the approximate factorization finite-difference 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 steady-state, two-dimensional 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;
- Navier-Stokes 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