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

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.