FreeCASE - Free(dom) Computational AeroServoElasticity

Last update:
January 15. 2016 14:05:15

Woodward & Colella

In this section we present the numerical results of AeroFoam solver for a 2D aerodynamic test problem, such as the inviscid compressible unsteady flow on the Woodward & Colella step.

Problem definition

Domain:

Rectangular channel of length L = 3 m and height h = 1 m
Rectangular step of height hS = 0.2 m at xS = 0.6 m

Material:

Polytropic Ideal Gas (PIG)
Specific heat ratio gamma = 1.4
Gas thermodynamic constant R = 0.714 J/kgK

Initial conditions:

Thermodynamic pressure Poo = 1 Pa

Temperature Too = 1 K
Mach number Moo = 3

Boundary conditions:

SupersonicInlet boundary conditions on the inlet section
ExtrapolatedOutlet boundary conditions on the outlet section
Slip boundary conditions on the top and bottom walls

Figure: Problem definition.

Space and time discretization

Space discretization:

Mesh created with Gmsh
# of rectangular cells Nv = 5040
# of nodes Nn = 10422

Time discretization:

Total simulation time endTime = 4 s
Timestep deltaT = 1.25e-3
Maximum Courant number maxCo = 1.00

Figure: Computational grid.

Numerical results

Comparison with CentralFoam solver and Woodward & Colella paper numerical results
Single iteration CPUtime = 0.04 s on AMD64 3500+ desktop PC with AMD Athlon 64 2.2 GHz CPU, 1 Gbyte RAM, 512 Kbyte L2 cache

Figure: Mach numer M distribution at t = 4.

Figure: Mach numer M distribution as a function of time t = 0 - 4 s

Download

Woodward&Colella.tar.gz test problem folder. Uncompress this archive in the OpenFOAM work folder and execute AeroFoam . Woodward&Colella from terminal to start the simulation. Download.

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