RVCQ3D (Rotor Viscous Code Quasi-3-D) is a computer code for analyzing
inviscid and viscous blade-to-blade flows in turbomachinery. It includes
the quasi-3-D effects of rotation, radius change, and variable stream surface
thickness. Simple flat plate and duct geometries can also be analyzed.
Formulation and differencing schemes
- Axial compressors and turbines
- Centrifugal impellers and radial diffusers (no splitters)
- Linear cascades
- Flat plates and rectangular ducts
- Fast parametric studies of blade shape, incidence angle, etc.
- CFD and turbomachinery education
RVCQ3D solves the Euler or Navier-Stokes equations written on a surface
of revolution. The equations are written in an (m,theta)coordinate system,
where m is the arc length along the surface and theta is the circumferential
direction. The stream surface radius and thickness are assumed to be known
functions of m, and are usually obtained from an axisymmetric throughflow
- Central difference + artificial viscosity
- Central difference + H-CUSP upwind
- AUSM+ upwind scheme
- Baldwin-Lomax (algebraic)
- Cebeci-Smith (algebraic)
- Wilcox's 2006 k-omega (two-equation) with cross diffusion term and stress limiter
All turbulence models include transition and roughness effects.
Input and output
- Explicit multi-stage Runge-Kutta scheme
- Variable time-step and implicit residual smoothing for convergence
- Preconditioning for low-speed (incompressible) flows
- Grids are usually generated using GRAPE
- Grid and solution files are in PLOT3D format
- Namelist input
- Printed output of convergence history, blade surface properties, and
average flow properties at the inlet and exit
Computer and graphics requirements
RVCQ3D requires a Fortran 90 compiler and CFD visualization software for
use. Click the button below for more information.
Test cases included with RVCQ3D 406
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Mach contours, NASA rotor 37,
70 percent span
Mach contours, NASA 6:1
Mach contours, Goldman annular
Flat plate skin friction
for testing turbulence models
Other cases modeled with RVCQ3D
Mach contours, supersonic flow through a slotted plate
Density gradient contours showing shocks
on a cascade of fan blades