An implicit finite difference code was developed which solves the transport equations for the turbulence kinetic energy and its dissipation rate in generalized coordinates in three dimensions. The finite difference equations are solved using the Beam-Warming algorithm. The kinetic energy-dissipation code, KEM, provides the closure; i.e., the turbulent viscosity for calculation of either compressible or incompressible flows. Turbulent internal flow over a backward-facing step has been calculated using the present code in conjunction with the Incompressible Navier-Stokes Code, INS3D. The results are in good agreement with experiments and two dimensional computations of other researchers
A generalized flow solver using an implicit Lower-upper (LU) diagonal decomposition based numerical ...
The fluid flow inside the space shuttle main engine (SSME) traverses through a complex geometrical c...
To support the National Aerospace Plane project, the RPLUS3D CFD code has been developed at NASA Lew...
An implicit, finite volume code for solving two dimensional, compressible turbulent flows is describ...
An upwind MUSCL type implicit scheme for the three-dimensional Navier-Stokes equations is presented....
An LU implicit multigrid algorithm is developed to calculate 3-D compressible viscous flows. This sc...
A new code aimed at the solution of three-dimensional internal laminar and turbulent compressible fl...
Critical to the advancement of computational aerodynamics capability is the ability to simulate flow...
The objective of this work is to develop, verify, and incorporate the baseline two-equation turbulen...
Abstract An implicit unfactored method for the coupled solution of the compressible Navier–Stokes e...
This project aims at developing a general purpose, user-friendly Computer code for numerical predict...
Three k–ω turbulence models using linear and nonlinear eddy-viscosity formulations are implemented i...
This project aims at developing a general purpose, user-friendly computer code for numerical predict...
Computation of the flow field inside a space shuttle main engine (SSME) requires the application of ...
Five viscous transonic airfoil cases were computed by two significantly different computational flui...
A generalized flow solver using an implicit Lower-upper (LU) diagonal decomposition based numerical ...
The fluid flow inside the space shuttle main engine (SSME) traverses through a complex geometrical c...
To support the National Aerospace Plane project, the RPLUS3D CFD code has been developed at NASA Lew...
An implicit, finite volume code for solving two dimensional, compressible turbulent flows is describ...
An upwind MUSCL type implicit scheme for the three-dimensional Navier-Stokes equations is presented....
An LU implicit multigrid algorithm is developed to calculate 3-D compressible viscous flows. This sc...
A new code aimed at the solution of three-dimensional internal laminar and turbulent compressible fl...
Critical to the advancement of computational aerodynamics capability is the ability to simulate flow...
The objective of this work is to develop, verify, and incorporate the baseline two-equation turbulen...
Abstract An implicit unfactored method for the coupled solution of the compressible Navier–Stokes e...
This project aims at developing a general purpose, user-friendly Computer code for numerical predict...
Three k–ω turbulence models using linear and nonlinear eddy-viscosity formulations are implemented i...
This project aims at developing a general purpose, user-friendly computer code for numerical predict...
Computation of the flow field inside a space shuttle main engine (SSME) requires the application of ...
Five viscous transonic airfoil cases were computed by two significantly different computational flui...
A generalized flow solver using an implicit Lower-upper (LU) diagonal decomposition based numerical ...
The fluid flow inside the space shuttle main engine (SSME) traverses through a complex geometrical c...
To support the National Aerospace Plane project, the RPLUS3D CFD code has been developed at NASA Lew...