RAE2822 transonic airfoil

Download mesh(structured mesh), Download mesh(BaramMesh)
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Link to youtube video

Introduction

This is a steady-state compressible flow example using a density-based solver. The RAE2822 airfoil transonic flow validation problem uses the conditions from the website below.

https://www.grc.nasa.gov/www/wind/valid/raetaf/raetaf01/raetaf01.html

A structured mesh of plot3d format is converted to OpenFOAM. You can also use mesh created using BaramMesh(Link to BaramMesh Tutorial). The far boundary consists of farfield in and farfield out and the airfoil name is wing.

The calculation conditions are as follows

  • solver : TSLAeroFoam
  • turbulence model : $SST$ $k-omega$
  • Mach number : 0.729
  • Angle of attack : 2.31 degree
  • farfield pressure : 108988 Pa
  • farfield temperature : 255.556 K
  • farfield turbulence : k = 0.08, omega = 7400

Start BaramFlow and load mesh

Run the program and select ‘New Case’ from the launcher. In the launcher, select [Density-based] for [Solver Type].

Use the given polyMesh folder. In the top tab, click [File]-[Load Mesh]-[OpenFOAM] in that order and select the polyMesh folder.

launcher

General

Set [Operating Conditions] as 0.

Models

For this example, we’ll use $SST$ $k-omega$ model for turbulence.

Materials

Set density as Perfect Gas, Viscosity as Sutherland.

Boundary Conditions

Set the boundary type and values as shown below.

  • wing
    • Wall – No slip, adiabatic
  • farfield_in, farfield_out
    • Far-Field Riemann
    • Flow Direction
      • Specification Method : AOA and AOS
      • Direction at AOA=0, AOS=0 : Drag direction (1 0 0), Lift direction (0 1 0)
      • Angle of Atteck : 2.31
      • Angle of Sideslip : 0
    • Mach Number : 0.729
    • Static Pressure : 108988
    • Static Temperature : 255.556
    • Turbulence : k and omega (k=0.08, omega=7400)

farfield Riemann

  • frontAndBackPlanes
    • Empty

Reference Values

Set values as follows

  • Area, Length : 0.3048(chord of airfoil)
  • Density : 1.4858(farfield condition)
  • Pressure : 108988(farfield condition)
  • Velocity : 233.6177(farfield condition)

Numerical Conditions

Set [Formulation] as [Implicit], [Flux Type] as [Roe-FDS] and [Entropy Fix Coefficient] as 0.5.

Set [Discretization Schemes] as [Second Order Upwind] for Flow and Turbulence.

Set [Convergence Criteria] as 1e-6 for Density.

Numerical Conditions

Monitor

Select [Add]-[Forces] and set values as follows

  • Flow Direction
    • Specification Method : AOA and AOA
    • Direction at AOA=0, AOS=0 : Drag direction (1 0 0), Lift direction (0 1 0)
    • Angle of Atteck : 2.31
    • Angle of Sideslip : 0
  • Center of Rotation : (0 0 0)
  • Boundaries : wing

Initialization

Enter the value and click the Initialize button at the bottom. Then click the [File]-[Save] menu to save the case file.

  • Velocity : (233.428, 9.416, 0)
  • Pressure : 108988
  • Temperature : 255.556
  • Turbulence
    • Scale of Velocity : 233.6177
    • Turbulent Intensity : 0.1
    • Turbulent Viscosity Ratio : 1

Run

Change the values as shown below, and click [Start Calculation] button.

  • Number of Iterations : 3000
  • Courant Number : 1000
  • Save Interval : 500
Residual graph

Post-processing

Click the parview button in [External tools] to open the paraview.

Change [Coloring] to p.

pressure contour