Dr. P. Hanley
PO Box 831514
Ocala, FL 34483
MultiSurface Aerodynamics Features
|Accurate Airfoil and Wing Analysis
MultiSurface Aerodynamics is based on a vortex lattice numerical
method (lifting surface/vortex ring approach).(Note: Other software
packages use the horseshoe vortex formulations which makes working with general
airfoil shapes difficult and time consuming). MultiSurface Aerodynamics can
easily test a complex wing that has multiple airfoil shapes along its span,
control surfaces, biplanes, hydrofoils, jib/main sail and a variety of
interacting surfaces. MultiSurface Aerodynamics can be used to estimate the
profile drag for each surface and has an option to adjust the surface lift
coefficient to account for airfoil stall (this is done using a built-in airfoil
analysis routine). This translates to more accurate results and less "trial
and error" work in the lab. The built-in analysis functions include:
3-D aerodynamics surface analysis using vortex lattice
method (based on vortex rings).
2-D airfoil analysis using linear-strength vortex panel method for
fast and accurate solutions.
Solution of boundary layer equations for computing section profile
drag, transition & separation points and stall prediction.
Computation of lift, drag and moment coefficients at specific angles
of attack for each surface.
Computation of local lift coefficient, induced angle of attack and
effective angle of attack for each surface.
Estimation of stall angle of attack for wings and airfoils. MultiSurface
Aerodynamics uses a formula based on theory and real life experiments to
determine the stall angle of attack.
Computation of intermediate airfoil sections and aerodynamics properties
for every lifting surface. This is done using the built-in Cross Section
Computation of stability and trim angle for multiple surfaces.
Computation of Cl_alpha & Cm_alpha for general
|Lifting Surface Design Tool
MultiSurface Aerodynamics provides all the components necessary for
rapid conceptual design and analysis of multiple aerodynamic surface
configurations. It is the only software package that can design multiple
wings using an interactive user interface that combines airfoil shapes, planform
definition and placement. Each surface can be assigned airfoils at its left
and right tips (the software actually solves the mean cambered surface based
on the airfoil camber lines). The Surface Editor can be used to:
Define and manipulate up to 30 aerodynamic
surfaces. Enter left and right chord lengths (taper), span length,
tip airfoils, twist angles, dihedral and sweep angles.
Use these surfaces as wings, tails, canards, winglets, sails, keels or in
a variety of other configurations.
Assign any airfoil shape to the left and right tips of each aerodynamic
surface. Choose from the built-in airfoil library or use your custom shapes.
The program will compute the lift, drag and moments based on these airfoil
Assign up to 32 X 32 vortex rings on each surface for accurate analysis.
With a choice of up to 30 indvidual surfaces, the program can use over 30,000
vortex rings to correctly model and solve your problem. Note: The
NACA Version can input only 16 surfaces.
Modify individual airfoil thickness and camber magnitudes.
Specify plain flap deflection and location for each airfoil.
Group selected surfaces and move them as a single unit.
Specify ground effect at an arbitrary height.
|Extensive Built-in Airfoil Library
Generate NACA 4-Digit and 4-Digit Modified, 5-Digit and 6-Digit
Analyze or Design Surfaces using over 1000 airfoils from the UIUC
Read in the coordinates of your custom airfoil and then
compute and compare its performance with the other airfoils in the database,
plot the shape or export them to .DXF files.
|Built-in Graphing Functions
MultiSurface Aerodynamics provides built-in presentation quality
graphing and reporting tools available in widely accepted aerodynamics formats.
Use these tools to communicate your results with the aerodynamics community,
engineers, designers, professors and manufacturers. The following functions
are provided by the software:
Graph local lift, induced angle of attack and effective
angle of attack versus y-location.
Graph lift, drag and moment coefficient as functions of angle of attack.
Graph lift coefficient versus drag coefficient for the system of
Generate lift versus angle of attack graphs. Use this graph to
quickly determine the angle for producing your required lift.
Generate lift and drag polar graphs for individual airfoils. These
curves show which airfoil can produce the required lift coefficient
but has the least amount of drag. Plot multiple curves to compare many airfoils
at the same time
Plot the nondimensional pressure difference distribution on 3-D surfaces.
You can also copy these plot to paste them into your report.
Copy any graph to the Windows clipboard and paste into any Windows
Export any graph using the .BMP file format.
Export Graph Values to ASCII files.
Export airfoils to .DXF file for use in a CAD program.
MultiSurface Aerodynamics generates tables of resuts for all surfacs and
for individual surfaces. Tables are also generated for graphed values.
allows you to:
Copy table values to the clipboard and paste into other
Save tables as ASCII files
New! Export tables
as .csv files. This function allows you to import tables into spreadsheet
programs and include the results of MultiSurface Aerodynamics into your existing
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