FreeCASE - Free(dom) Computational AeroServoElasticity |
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Oblique shockIn this section we present the numerical results of AeroFoam
solver for a very simple 2D aerodynamic test problem, such as the reflection of an oblique shock.
Problem definition- Domain:
- Rectangular channel of length L = 4.17 m and height h = 1 m
- Material:
- Polytropic Ideal Gas (PIG)
- Specific heat ratio gamma = 1.4
- Gas thermodynamic constant R = 287.05 J/kgK
- Initial conditions:
- Thermodynamic pressure Poo = 101325 Pa
- Temperature Too = 288.15 K
- Mach number Moo = 2.9
- Boundary conditions:
- SupersonicInlet boundary conditions on the inlet section (front and top walls)
- ExtrapolatedOutlet boundary conditions on the outlet section
- Slip boundary conditions on the bottom wall
Figure: Problem definition.
Space and time discretization- Space discretization:
- Progressively refined meshes created with blockMesh
- # of rectangular cells Nv = 400 - 1600 - 6400 - 25600
- # of nodes Nn = 451 - 1701 - 6601 - 26001
- Time discretization:
- Total simulation time endTime = 0.01 s
- Timestep deltaT = 4e-5 - 2e-5 - 1e-5 - 5e-6 s
- Maximum Courant number maxCo = 1.95

Figure: Computational grid. Numerical results- Comparison with exact solution and with OpenFOAM built-in inviscid compressible solvers rhoSonicFoam, rhopSonicFoam and sonicFoam
- Single iteration CPUtime = 8.16e-3 - 2.07 e-2 - 6.11e-2 - 2.22e-2 s on AMD64 3500+ desktop PC with AMD Athlon 64 2.2 GHz CPU, 1 Gbyte RAM, 512 Kbyte L2 cache
Figure: Thermodynamic pressure P contours at t = 0.02. Table: Comparison of the accuracy and efficiency performances of the evaluated solvers.  Figure: Thermodynamic pressure P contours as a function of time t = 0 - 0.02.Download- ObliqueShock.tar.gz test problem folder. Uncompress this archive in the OpenFOAM work folder and execute AeroFoam . ObliqueShock_AeroFoam from terminal to start the simulation. Download.
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