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 Tool. Computation of stability and trim angle for multiple surfaces. Computation of Cl_alpha & Cm_alpha for general configurations.

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 shapes. 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 Airfoils. Analyze or Design Surfaces using over 1000 airfoils from the UIUC airfoil database. 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 surfaces. 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 program. 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.

Built-in Tables MultiSurface Aerodynamics generates tables of resuts for all surfacs and for individual surfaces.  Tables are also generated for graphed values.  Multisurface Aerodynamics allows you to: Print tables Copy table values to the clipboard and paste into other applications. Save tables as ASCII files 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 projects. How to Purchase

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