NACA 0012 airfoil

Problem definition

• Domain:
  
• Internal NACA 0012 airfoil subdomain with chord c = 1 m
  
• External circular subdomain with radius Roo = 25 m >>  c
• Material:
  
• Polytropic Ideal Gas (PIG)
• Specific heat ratio gamma = 1.4
• Gas thermodynamic constant R = 287.05 J/kgK
• Initial conditions: 
• Thermodynamic pressure Poo = 85419 Pa
  
• Temperature Too = 260.00 K
• Mach number Moo = 0.5 - 0.75
• Angle of attack alpha = 0 - 2 - 4 deg
  
• Boundary conditions:
• Slip boundary conditions on internal subdomain
• Riemann boundary conditions on external subdomain

Space and time discretization

• Space discretization:
• Mesh created with Gmsh
• # of triangular cells Nv = 6620
  
• # of nodes Nn = 6864
  
• Time discretization:
• Total simulation time endTime = 0.035 s
• Timestep deltaT = 5e-6 - 2.5e-6 s
  
• Maximum Courant number maxCo =  1.95

Figure: Computational grid.

Numerical results

• Comparison with FLUENT solver and AGARD 138 report experimental results
  
• Single iteration CPUtime = 0.045 s on AMD64 3500+ desktop PC with AMD Athlon 64 2.2 GHz CPU, 1 Gbyte RAM, 512 Kbyte L2 cache

Figure: Pressure coefficient Cp contours at Moo = 0.75 and alpha = 4 deg.



Figure: Pressure coefficient Cp distribution.

Download

• NACA0012.tar.gz test problem folder. Uncompress this archive in the OpenFOAM work folder and execute AeroFoam . NACA0012_7k_M050_a0 from terminal to start the simulation. Download.