YF17 fighterIn 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 YF17 fighter. Problem definition Domain:
 Internal YF17 halfmodel 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 = 46040 Pa
 Temperature Too = 248.00 K
 Mach number Moo = 0.28
 Angle of attack alpha = 19.4 deg
 Boundary conditions:
 Slip boundary conditions on internal subdomain
 SupersonicInlet boundary conditions on airduct and engine boundary subpatches compatible with a turbofan engine total thrust of T = 28e3 N
 SymmetryPlane boundary conditions on symmetry plane
 Riemann boundary conditions on external subdomain
Figure: Wind tunnel model for the YF17 fighter.
Space and time discretization Space discretization:
 Mesh downloaded from CGNS repository (many thanks to Bruce Wedan) and then converted in Gmsh format with a small utility written in SciLab
 # of tetrahedral cells Nv = 528515
 # of nodes Nn = 97104
 Time discretization:
 Total simulation time endTime = 0.2 s
 Timestep deltaT = 1.25e6 s
 Maximum Courant number maxCo = 1.95
Figure: Computational grid. Numerical results Comparison (only qualitative) with F18 HARV flight test visualizations
 Single iteration CPUtime = 5.10 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 and streamlines.
Figure: Pressure coefficient Cp contours. Download YF17.tar.gz test problem folder. Uncompress this archive in the OpenFOAM work folder and execute AeroFoam . YF17_530k_M028_a19 from terminal to start the simulation. Download.
