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Airfoil Analysis
3D Wing Analysis
Euler/NavierStokes
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The price for the perpetual license of MultiElement Airfoils
 Lite is $395. Please click the link below to purchase the software.
MultiElement AirfoilsLite Edition requires Microsoft Windows XP,
Vista, 7 or 8.
Details
MultiElement Airfoils (Lite Edition) is a computer
aided engineering (CAE) tool for calculating the aerodynamics of isolated
or multiple airfoil shapes interacting in a flow field. Engineers and design
professionals use it to rapidly and accurately compute many aircraft,
marine and automobile flow scenarios on an ordinary Windows based PC or notebook
computer.
MultiElement Airfoils Lite Edition is based on a linear strength
vortex panel method for the inviscid flow solution. It solves the boundary
layer equations to compute profile drag and to determine the location of
the transition and separation points for each airfoil in the flow field.
The program also uses a stall model based on the separation points locations
to account for reduction in the lift prior to airfoil stall.
MultiElement Airfoils (Lite Edition) is an excellent reference and
educational resource. Its airfoil library contains NACA 4, 5 & 6digit
airfoils, the entire UIUC airfoil database and the ability to import custom
airfoils. It is an interactive alternative to textbooks, handbooks, internet
research, differential equations solutions and error prone "pencil and paper"
calculations.
Students at universities, high schools and elementary schools can
use MultiElement Airfoils as a virtual lab to investigate many real world
problems in science and engineering. The software can export airfoils
and airfoil combinations to .DXF files. It can accurately plot airfoil templates
for use in model airplane construction.
Features
MultiElement Airfoils (Lite Edition) enables you to:

Position and analyze up to 20 airfoils in a single computation.

Read in the coordinates of your custom airfoil that you designed
specifically for your general aviation airplane, rudder, spoiler or propeller.
The program import text files or drawings in the .DXF file format
(line and arc entities).

Generate all NACA 4Digit and 4Digit Modified Airfoils. With the
NACA generator, you can set the thickness,
camber location and magnitude. You can create numerous airfoils for testing
and experimentation.

Generate the NACA 5Digit family of airfoils.Create NACA 210XX, 220XX,
23XXX, 240XX, 250XX, NACA 211XX, 221XX, 231XX, 241XX and 251XX series airfoils.
This generator gives you a different family of airfoil for
experimentation.

Generate NACA 6Digit family of airfoils. With the NACA generator,
you can select and generate NACA 63XXX, 64XXX, 65XXX, 66XXX, 63AXXX,
64AXXX, 65AXXX airfoils.

Analyze any of the airfoil in the
UIUC airfoil database.
The database contains Selig, SD, MH and Eppler airfoils amongst others.

Compute lift, drag and moment coefficients at your specific angle
of attack. See how the airfoils perform when you vary the angle of
attack.

Compute profile drag coefficient at your specific angle of attack.
The profile drag is a combination of the friction and pressure drag. The
profile drag depends on Reynolds number and whether or not the flow is laminar
or turbulent. Use MultiElement Airfoils (Lite Edition) to see how the location
of the transition point affects the drag.

Estimate vehicle's lift and profile drag based on wing dimensions,
fluid (water or air) and velocity.

Estimate stall angle of attack. MultiElement Airfoils (Lite
Edition) uses a formula based on theory and real life experiments to determine
the stall angle of attack.

Estimate lift coefficient near the stall point (prior to stall). The
above formula is also used with the computed lift to determine the reduction
in lift close to stall.

Generate lift and drag polar graphs. These curves show which
airfoil can produce your required lift but have the least amount of drag.
Plot multiple curves to compare many airfoils.

Generate lift versus angle of attack graphs. Use this graph to
quickly determine the angle for producing your required lift.

Plot streamlines over the airfoil  you can copy plots to paste in
your reports.

Plot pressure distribution contours in the flow field  you can also
copy these plot to paste in your report.

Export single airfoils to .DXF file for use in a CAD
program.

Export single airfoil coordinates to ASCII file.

Plot single airfoils to any dimension using your windows support
printer. This is useful for constructing plans for building wings
and hydrofoils.

Copy a high resolution screen shot of all your graphs for inclusion
in your reports and presentations.

Print Tables and Graphs.

Free technical support for one year after purchase.
Purchase
The price for the perpetual license of MultiElement Airfoils
 Lite is $395. Please click the link below to purchase the software.
MultiElement AirfoilsLite Edition requires Microsoft Windows XP,
Vista, 7 or 8.
Requirements
MultiElement Airfoils (Lite Edition) requires a PC running Windows
XP, Vista, Version 7 or 8. Technical
Questions can be emailed to
hanley@hanleyinnovations.com.
See Also:
MultiElement Airfoils 5.0,
MultiSurface
Aerodynamics,
VisualFoil
Plus
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19962015 
