
RAE A plane
In this section we present the numerical results of AeroFoam solver for a 3D aerodynamic test problem, such as the inviscid compressible unsteady flow around a RAE A plane. Problem definition Domain:
 Internal RAE A wing + axisymmetric body subdomain
 External hexahedral subdomain of size 14 m x 12 m x 12 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 = 29765 Pa
 Temperature Too = 275.38 K
 Mach number Moo = 0.9
 Angle of attack alpha = 1 deg
 Boundary conditions:
 Slip boundary conditions on internal subdomain
 Riemann boundary conditions on external subdomain
Figure: RAE A wing + axisymmetric body subdomain geometry. Space and time discretization Space discretization:
 Mesh created with GAMBIT
 # of tetrahedral cells Nv = 459487
 # of nodes Nn = 95668
 Time discretization:
 Total simulation time endTime = 0.02 s
 Timestep deltaT = 2e7 s
 Maximum Courant number maxCo = 1.85
Figure: Computational grid. Numerical results Comparison with FLUENT solver and AGARD 138 report experimental results
 Single iteration CPUtime = 4.52 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.
Figure: Pressure coefficient Cp distribution. Download RAEplane.tar.gz test problem folder. Uncompress this archive in the OpenFOAM work folder and execute AeroFoam . RAEplane_460k_M090_a1 from terminal to start the simulation. Download.

