FreeCASE - Free(dom) Computational AeroServoElasticity |
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YF-17 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 YF-17 fighter. Problem definition- Domain:
- Internal YF-17 half-model 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 sub-patches 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 YF-17 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 = 1.25e-6 s
- Maximum Courant number maxCo = 1.95

Figure: Computational grid. Numerical results- Comparison (only qualitative) with F-18 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.
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