3D Wing Analysis
Full Version $189 |
Download software after purchase. No shipping & handling. VisualFoil 5 requires Windows XP, Vista, 7 or 8.
VisualFoil 5.0 is a modern easy-to-use airfoil analysis and
design software for Windows XP, Vista & 7. The NACA Version
is suitable for most users who need to analyze and obtain data for NACA airfoil
shapes. Expert users can analyze and test the performance of their
custom designs with the Full version of VisualFoil 5.
VisualFoil can quickly and inexpensively determine the best cross
section shapes for wings, spoilers, struts, hydrofoils,
keels, rudders and other aerodynamic and support structures.
Feature of VisualFoil 5 Include:
Incompressible flow solver using vortex panel method coupled with
boundary layer solver for computing lift, drag and moment
Built-in library of NACA 4, 5 & 6-digit airfoils
Custom airfoil analysis and modification. VisualFoil reads in a text
file with the airfoil coordinates and then finds the aerodynamics
Custom airfoil editor with .DXF file input. Software reads in
line and arc entities and then finds the aerodynamic coefficients of the
Computes and graphs Cl, Cd & Cm versus angle of attack.
Stall model to predict the maximum lift coefficient and angle of attack
for maximum lift.
Export tables to .csv files
Export airfoil to .dxf files
Note: The NACA version of VisualFoil 5.0 does not
read-in custom airfoils & .DXF files. It will analyze
and modify NACA 4, 5 & 6-digit airfoils and generate lift, drag and moment
coefficients. It can export and plot these airfoil shapes.
Linear strength vortex panel method
Coupled boundary layer solver to compute profile drag.
Lift, drag & moment coefficient calculations.
Prediction of transition & separation points to demonstrate the
validity of your calculations.
Stall & maximum lift prediction
Surface graphs of pressure coefficient & velocity ratio
for clear explanations of the boundary layer behavior.
Beautiful color contour graphs of the pressure coefficient for your
reports and presentations.
Custom graphs of Cl, Cd & Cm versus angle of attack that you can
use in your homework assignments and final reports
Multiple graphs of Cl vs Cd for explanining why you picked one airfoil
over the other.
VisualFoil can predict profile drag and stall.
Compare the performance of many airfoils on a single
VisualFoil has an extensive library of airfoils.
VisualFoil graphs Cp at various Angles of Attack.
VisualFoil is an excellent educational tool for K-12 &
The price of the full version of VisualFoil 5.0 is $189 US. The NACA
version (only NACA 4, 5 & 6-digit airfoils) is
$69 $29 US. Please use
the link below to purchase the software.
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