FreeCASE - Free(dom) Computational AeroServoElasticity
Last update:
January 31. 2013 07:50:49

NACA 0012 airfoil

In this section we present the numerical results of AeroFoam solver for a 2D aerodynamic test problem, such as the inviscid compressible unsteady flow around a 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


Figure: Problem definition.

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.




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