Program MyFoil

MyFoil is an interactive program created to help you design and analyse subsonic isolated airfoils. It enables you to design an airfoil fast and easy while having reference to its streamlined characteristics. Overall, the results are accurate enough for the model aircraft design and the good alternative to expensive Wind Tunnel testing.

MyFoil allows you to:

  • Simply create a new airfoil with mouse (drag and drop)
  • Compare different streamlined characteristics
  • Flip airfoil (for an upside-down flight)
  • Display a zoom leading/trailing edge
  • Display a curvature of an airfoil
  • Display a pressure distribution
  • Obtain lift, moment and drag coefficients (Cl, Cm, Cd )
  • Display a polar curves for each of Reynolds number
  • Print an airfoil (tip, root or current)
  • Export to DXF format (only commercial version)
  • Save and load data of an airfoil in MyFoil format
  • Save and load airfoil coordinates in UIUC Archive format (*.DAT)
  • Save and load polar in MyFoil format

MyFoil is a very fast program for airfoil analysis. File size 993 KB, no installation.

System requirements: Windows XP or higher

MyFoil mainscreen


Calculation Methods

The streamlined parameters of an airfoil are described with three fundamental coefficients:

Cl Lift coefficient

Cd Drag coefficient

Cm Pitching moment coefficient

MyFoil first computes the inviscid incompressible potential flow about a 2-D airfoil using the vortex panel method for obtaining the pressure distribution and the lift and moment coefficients. Set of linear equations is solved using a fast LU decomposition.

Airfoil is then placed in a low-speed viscous flow and the results of previous method (especially the velocity distribution) are used to compute the boundary layers on the two surfaces of the airfoil. The boundary layer model is used to obtain the drag coefficient. The boundary layer formulation consists of a model for the laminar part of the flow, a transition criterion, and a model for the turbulent part of the flow. MyFoil uses for the laminar part the Thwaites' one equation method and the Head's two equations method for the turbulent part. Michel's criterion is used to locate a transition from laminar to turbulent flow.

Compare polar curves

MyFoil enables you to download external polar curves to compare them with different airfoils, but only in a special format. So it is necessary to download external airfoil first and then save its polar curves (in given Reynolds numbers) in MyFoil format. It is possible to display three external polar curves at the same time.
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