VisualFoil Plus solves the 2D compressible Euler equations and computes the
lift, drag and moment coefficients for airfoils in subsonic, transonic and
supersonic flows. It generates accurate aerodynamics data for experimental
or existing airfoils where the information might be incomplete or unknown.
VisualFoil Plus analyzes and selects airfoils for jet aircraft, propellers, silent UAV propellers,
industrial machinery and other products.
VisualFoil Plus has a library of 1000s of built-in airfoils which includes
NACA 4, 5 & 6-digit airfoils. In addition, the user can enter
**custom** airfoils for analysis and **modify** existing airfoil
shapes.

- 2-dimensional compressible Euler equations using a finite-volume solver
- 2nd order flux vector splitting
- 4-stage Runge-Kutta time marching scheme using local time steps
- Automatic o-grid generation
- Linear strength vortex panel method for incompressible flow calculations
- Coupled boundary layer solver for profile drag calculations
- Contour plots of pressure, Mach number, temperature & total pressure
- Surface plots of Cp, Mach number, velocity ratio & temperature

A poorly performing airfoil will result in a poorly performing wing and noisy propeller. If you are designing a wing or propeller for a UAV, light aircraft, or car, VisualFoil will provide the absolute best start for your project. VisualFoil Plus is used to determine the airfoil drag divergence Mach number that improves the performance of propellers and high speed aircraft designs.

Visual Foil Plus can be used to compute the drag divergence Mach number for any airfoil shape using subsequent runs over a range Mach number. The above figure shows drag divergence for a NACA 0012 airfoil at zero angle of attack.

VisualFoil Plus requires a PC, Laptop or tablet running MS Windows XP, Vista, 7, 8 or 10. The subscription cost is $89 for one month.

Do not hesitate to email or telephone us at (352) 261-3376 if you have any questions.