In 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

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.