Viewing Results


Once the case successfully solves, the data will be 'Published' on the main project results page. You will be able to access this summary information by clicking on the project name at the top of the left navigation panel. Clicking on the individual run will take you to the results page specifically for that run.

You can view the results 2 different ways: 3D Interactive Viewer or Viewing Results and Images on Interface.

Contents of this Page

Important! While all results you see through the app (images/movies/tabular data) is stored long-term, the underlying completed simulation data may be deleted after around 6 months as the scratch storage on the supercomputer system is eventually cleaned up. What this means is that if you require custom data from a simulation you will want to let us know before or after running a simulation. We won't be able to necessarily access the data after a period of time after it has run.

Notes on Results

TSAero - 2D Airfoil Tool

Results are presented in Coefficient form. Lift Coefficient, Drag Coefficient, and Moment Coefficient about the quarter chord.

The Moment Coefficient is transferred to the quarter chord during post processing. If you plot or download the Moment Coefficient history from the Curves page, the moment is located at (0,0).


Below is a list of variables that may be included in your results. All of the forces and moments are reported in Newtonian units.

  • Cp/pGauge: Surface Pressure magnitude
  • Cf/tauw/tauwMean: Skin friction coefficient, Surface Shear Stress or Average Surface Shear Stress
  • Uw/UwMean: Velocity or Average Velocity
  • CpT/pTot: Total Pressure
  • U/NormalisedU: Velocity or Normalized Velocity

Note: pTot, pGauage, pX, pY, and pZ will be normalized by the freestream velocity if the input is greater than 1 m/s.

Interactive Viewer

Along with viewing the images and movies by cycling through the tabs on the results page, users will also have the option to view results through our Interactive Viewer. The results in the Interactive Viewer are exactly the same in the images/movies tab, but you are able to rotate around the vehicle as you view your results. You can read more about the Interactive Viewer here. Note: If you choose to use the interactive viewer, we recommend using it in Chrome browser.


Forces Summary

In the Total Forces table, you will find the total Lift , Drag, and Pitching Moment Coefficients (about the quarter chord) and the Lift/Drag ratio calculated for your airfoil.

Monitored Patches are not used for the 2D Airfoil.

Under the Individual Force Groups, you will find 2 tabs: Drag and Lift. This table will show the Drag and Lift breakdowns for each element if you have a multiple element airfoil.

At the bottom of the page is the convergence history for Lift and Drag. Clicking on the graph allows you to view the full convergence history.


In the Images tab, you will find POSTPRO images for your Run.

  • Select the type of image you want to see and then a thumbnail of the image pops up.
  • Click the thumbnail to see a larger image of the plot

CpT Images are available with the airfoil in 2 positions:

  • CpFluidSlice: this always has the airfoil chord positioned such that the chord is horizontal (how the coordinates are input) - this means that if the airfoil is at angle of attack the free stream flow direction is rotating. This can be harder to visualize (Top image on the right); therefore, the CpFluidSliceAOA was created.
  • CpFluidSliceAOA: during postprocessing the image is rotated in the frame showing the airfoil at the run angle of attack - this means the freestream flow direction is always horizontal. (Bottom image at the right - airfoil is at 14 deg angle of attack.)

Also available is the Cp distribution plotted against the x/c. Cf plots will be added soon.


2D Airfoil runs do not have any movie post processing. Movies are used to visualize slices across a geometry and because airfoils are by definition 2D there is no variation spanwise across the geometry.


In the Curves tab, you will find the convergence history for all the forces as well as residual plots. Note the second curve that starts 2000 iterations into the run this is the average force and it is averaged over 2000 iterations for the 2D airfoil.