Item Description :

Super_Foil® is a single file , 3.3k lines of hard coded algorithm that solves the subsonic inviscid incompressible flow field , as well as , the supersonic compressible viscous flow field , about arbitrary two dimensional surfaces . Using six different analytical , numerical and computational mathematical methods

Geometry Modeling :

- One series airfoils
- Four series airfoils , standard and modified thickness
- Five series airfoils , standard and modified thickness
- Five series reflexed airfoils , standard and modified thickness
- Six series airfoils , standard and modified mean lines
- Joukowski airfoils
- Von-Karman airfoils
- Variable axes sections
- Plus a saved library of 1420 different airfoil file
- Four paneling schemes (normal distribution , full cosine spacing , half sine spacing , half cosine spacing )
Automatic Grid Generator :

- Flat panels on the mean line
- Flat panels on the complete outer surface
- Unstructured triangular grid for the full domain
- Structured elliptic partial differential grid for the full domain
Aerodynamic Solver :

- Analytic Thin Airfoil Theory

- Numerical Concentrated Lumped Vortex Panel Method

- Numerical Surface Distribution Constant Source + Constant Vortex Panel Method

- Numerical Surface Distribution Linear Vortex Panel Method

- Numerical Integration of The Potential Flow Equation In Full Domain , Using 5'th Order Dormand-Prince Integrator On Triangular Grid

- Supersonic , Compressible , Viscous Complete Navier-Stokes Equations , Using Time Marching Accurate MacCormack Finite Difference Method On Elliptic Grid
Outputs :

- Surface and mean-line paneling geometry
- Center of pressure location
- Lift , drag , moment , heat , temperature , density , shear
- Trangular grid with numbering , dimensions and order
- Subsonic inviscid incompressible pressure and velocity fields
- Elliptic partial differential grid
- Supersonic viscous compressible flow :

- Axial velocity
- Normal velocity
- Shear stress in xx
- Shear stress in yy
- Shear stress in xy
- Heat flux x-component
- Heat flux y-component
- Dynamic viscosity
- Normalized pressure
- Mach number
- Normalized velocity
- Normalized temperature
Test case NACA 0006 at sealevel , mach five , 50k panels :

- Grid time : 0.25028 seconds
- Solver time : 4.803 minutes
- Using Intel core i3 - 3.3 GHz processor , 16 GB of ram drive

Test case NACA 64008 at sealevel , Mach two to five , 65k elliptic panels

Dear Colleague :

- Installing cad/cam package/s takes too much time and space , building the model itself takes too much time and efforts, preprocessing/post processing and the processing itself , all takes too much time and effort

- Super_Foil® solves the Concentrated , Surface Distribution and the Full Domain Aerodynamics , using six different aerodynamic techniques , in subsonic incompressible inviscid flow field as well as supersonic compressible viscous fields. Takes less than 1 sec to generate model/automatic grid/solver and results , for supersonic regimes it takes less than five min to generate a dense grid and solve it !!
Super_Foil® License Is For One Year , For One Machine.