Program AeroFoil :

Calculates The Potential Flow About NACA Four Series Airfoils By Means Of The Classical This Airfoil Theory Together With Two Different Surface Distribution Panel Methods

Program Abilities :

• The Classical Thin Airfoil Theory
  Assumes A Trigonometric Vortex Distribution Along The Airoil Camber Line In Polar Coordinate System , Accounts Only For The Camber Line Geometry , Does Not Consider The Airfoil Thickness At All
  Also , The Moment Coefficients Don't Depend On The Angle of Attack
  Here We Solve For The second Order Camber Equations Only

• Constant Source Plus Constant Vortex Surface Distribution Panel Method
  Where The Constant Vortex Distribution Is The Same On Each Panel And Use Its Value To Adjust The Trailing Edge Flow , While Allowing The Constant Source Distribution Together With This Vortex To Vary For Each Panel To Satisfy The No Flow Conditions At The Center Of Each Panel

• Linear Vortex Panel Method Which Is Equivalent To The Quadratic Strength Doublet Distribution Where We Can Equalize The Trailing Edge Flow By Considering The Same Vortex Strength At The Most Aft Upper And Lower Panels (Same Vortex But Different Sign)