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Angle of Attack Calculator






 

 

 


How This Is Calculated


$$ \alpha = {tan}^{-1} \left( \frac{h}{c} \right) $$ where:

α   =   Angle of attack   (°)

h   =   Height of the foil above the referecne plane   (m)

c   =   Chord length   (m)


Assumptions


  • Flow is steady and two dimensional.
  • Fluid is incompressible.
  • Foil is thin.
  • Viscous effects are ignored.
  • Angle of attack is below stall angle.


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