Item Description :

1- Two Dimensional Geometry Package :

- Calculates ordinates for the following :

- NACA symm/cambered one series
- NACA symm/cambered four series with standard/modified thickness
- NACA five series with standard/modified thickness
- NACA reflexed five series with standard/modified thickness
- NACA symm/cambered six series with standard/modified mean line
- Joukowski airfoils
- Von-Karman Trefftz airfoils
- Variable axis elliptical sections
- Built-in library of 1490 different airfoil

- Automatic paneling with four different schemes

- Uniform spacing
- Full cosine
- Half cosine
- Half sine

- Ability to invert any airfoil up-side-down

- Option to write a geometry file
2-

Three Dimensional Geometry Package :

- The 3D Geometry Package calculates ordinates for any number of non lifting bodies using the following methods :

- Frame by frame method
- Rotate two different parametric numeric or symbolic curves in space to generate a body of revolution . Two curves to generate the upper and lower parts separately

- Option to change any point on any frame at any body

- The 3D Geometry Package reads symbolic equations and numeric numbers

- No restriction for the number of panels nor the spacing scheme as the package curve fits and surface fits all the surfaces

- The 3D Geometry Package uses the lofting method to construct lifting surfaces with any cross-section you want , with Any number of wings , any number of partitions for each wing

- Each wing may have different twist pivot

- Each partition on each wing may have different sweep pivot , sweep angle , twist and dihedral angles

- Each partition may have any airfoil family on the same wing

- Leading or trailing edge control surface for any partition at any wing

- Ability to change any local axes in the main global axes

- Different options for paneling location for lifting surfaces :

- Around the actual surface
- On the mean cambered surface
- At the chord plane

- Trailing vortices extend from each bound vortex :

- To a distance downstream
- To the panel trailing edge , then to a distance downstream
- To the panel trailing edge then to the partition trailing edge , and finally to a distance downstream

- Trailing vortices extension :

- Parallel to the x-axis
- Parallel to the free-stream

- The package automatically calculates the Mean aerodynamic chord length and position with the center of gravity and inertia tensor for the complete model

- Center of gravity location depends on area/ mass distribution

- Option to export your model to :

- Ansys 3d curves files .dat
- Datcom+ input files .dcm
- Matlab .m files
- Matlab binary files .mat
- Unigraphics spline files .dat
- Virtual reality model file .wrl
- VlAERO input file .vlp