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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