wiki:EXNAeroDemoCases/naca0012

NACA0012 Aerofoil

Applications

  • Aeronautics
  • Wind Energy

Capabilities covered in this demonstration

  • Incompressible Flow
  • Transient

Description & Performance Data

A SST RANS simulation of incompressible, isothermal air flow around a NACA0012 Aerofoil.

Mesh Topology:

Multi-Block structured

Data Type:

Structured

No. Control Volumes:

14 million

Precision:

Double in near-body blocks

GPU Type:

Nvidia K20

No. GPU Devices:

1

GPU memory usage:

CPU Type:

Intel Xeon

No. CPU Devices:

2

Notes

EXN/Aero has the capability to solve external aerodynamics problems in either incompressible or compressible modes. Both transient and steady state solvers are also available. The present simulations were run using the transient solver for incompressible flow around a NACA0012 aerofoil. Incidence angles varied between 0, 3, 5, 7, 9, and 10 degrees. Freestream turbulence intensity was set to 0.05%. The velocity and pressure fields computed using EXN-Aero are shown below. Comparison can be made to the published data [2] has been shown in table below.

EXN/View: Mesh, Physics and Solver Settings

This is a navigable instance of the actual EXN/Aero user interface, showing the mesh at right and the solver control tree at left. Expand nodes in the tree to see an how we set up the physics models and solver parameters. The demonstration case shown here can be reconstructed on any terminal where EXN/Aero is installed, using the files found below.

Data Files

naca0012.cgns
Solver_Control.xml
Variables.xml
Monitor.xml
Database.xml
BC_Families.xml
Options.xml
Tooltips.xml
Overset.xml
Cell_Families.xml
cvc.log
Info.txt

Tutorial

Tutorial sessions can be found at: http://envenio.ca/wiki/

Results

Velocity Field and Pressure Field.

Lift and Drag Results

Keywords

  • NACA0012
  • SST-RANS
  • Incompressible
  • [1] NASA, 2D NACA 0012 Airfoil Validation Case; Link: https://turbmodels.larc.nasa.gov/naca0012_val.html
  • [2] Ladson, C. L., 'Effects of Independent Variation of Mach and Reynolds Numbers on the Low-Speed Aerodynamic Characteristics of the NACA 0012 Airfoil Section,' NASA TM 4074, October 1988
  • [3] McCroskey?, W. J., 'A Critical Assessment of Wind Tunnel Results for the NACA 0012 Airfoil,' AGARD CP-429, July 1988; also NASA TM 100019, October 1987
Last modified 4 weeks ago Last modified on Sep 21, 2017 1:58:42 PM

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