ONERA M6 transonic wing

Download mesh
Download simulation

Introduction

intro

This example is a steady-state compressible flow analysis using a density-based solver. As a validation problem for the ONERA M6 wing, the calculation conditions from the following site are used.

https://www.grc.nasa.gov/WWW/wind/valid/m6wing/m6wing.html

intro

intro

Pressure coefficient for each section of the wing in the span direction

A structured mesh is converted to OpenFOAM.

Simulation conditions are as follows

  • solver : TSLAeroFoam
  • turbulence model : $SST$ $k-omega$
  • Mach number : 0.8395
  • Anglf of Attack : 3.06 degree
  • farfield pressure : 315979 Pa
  • farfield temperature : 255.56 K
  • farfield turbulence : k = 2.714, $omega$ = 131360

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.

  • Wall-wing-1, Wall-wing-2
    • Wall – No slip, adiabatic
  • sym-1, sym-2, sym-3, sym-4
    • symmetry
  • inlet-1, inlet-2, outer-1, outer-2, outlet-1, outlet-2
    • Far-Field Riemann
    • Flow Direction : direction of AOA 3.06 (0.998574, 0.053382, 0)
    • Mach Number : 0.8395
    • Static Pressure : 315980
    • Static Temperature : 255.56
    • Turbulence : k and omega(k = 2.714, omega = 131360)

farfield Riemann 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]-[Density의] as 1e-5.

Numerical Conditions

Monitor

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

  • Lift Direction : (-0.053382, 0.998574, 0)
  • Drag Direction : (0.998574, 0.053382, 0)
  • Boundaries : wall-wing-1, wall-wing-2

Initialization

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

  • Velocity : (268.647, 14.361, 0)
  • Pressure : 315980
  • Temperature : 255.56
  • Turbulence
    • Scale of Velocity : 269.031
    • 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

When the calculation is started, you can see the graphs of Residuals and Force monitor as shown below.

Residual graph

Post-processing

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

Change [Coloring] to p.

pressure distribution