VisualFoil Plus

VisualFoil 5

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 aircraft, water craft, 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.

Flow Solvers

  • 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. If you are designing a wing for a UAV, light aircraft, or car, VisualFoil will provide the absolute best start for your project. The same is true for keels, rudders and hydrofoils.High endurance, range and speed capabilities demand high performance airfoils. VisualFoil Plus can be used to airfoil drag divergence for propellers and high speed aircraft design.

Real-time Transonic Airfoil Analysis

Built-in Tools and Solutions

2D Compressible Euler Solver

Linear-Strength Vortex Panel Solution

Accurate Stall Model

Click-to-Modify Airfoil Function

NACA 4, 5 & 6 Digit Airfoil Tool

Built-in UIUC Airfoil Database

Custom Airfoils (Text/DXF File Import)

Precision Airfoil Plotting Utility

Printable Airfoil Performance Report

Cp and Velocity Ratio Surface Plot

Cl, Cd & Cm versus Angle of Attack Plot

Lift/Drag Polar Plot

Plot of Flow Field Pressure

Airfoil Pressure Vector Plot

Streamline Plots

Flow Field Probe & Particle Trajectory

The Drag Divergence Mach Number

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 Subscription

VisualFoil Plus requires a PC, Laptop or tablet running MS Windows XP, Vista, 7, 8 or 10. The annual subscription cost is $695 per year.

Subscribe for $695 per year