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MultiSurface Aerodynamics
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MultiSurface Aerodynamics Validation

MultiSurface Aerodynamics is an accurate and easy-to-use software package for analyzing multiple lifting surfaces.  It is based on the vortex-lattice method which provides the most ideal trade-off between accuracy and speed for aerospace, automotive and marine analysis & design.  Most vortex lattice codes are not equipped with Hanley's proprietary methods for computing profile drag and stall. These competing software cannot provide the user with essential  preliminary wing design parameters such as minimum profile drag, maximum lift/drag ratio, maximum lift & estimates of the stall angle of attack.

MultiSurface Aerodynamics can be used to compute lift, drag (profile and vortex), moments and longitudinal stability. We compared results of the MultiSurface Aerodynamics program with experimental data reported by James C. Sivells in NACA TN 1422. The follow is a summary of the results for the NACA 65-210 airfoil with two degrees of washout:

  MultiSurface Aerodynamics    Experiment     % Difference  
Cl_max

1.297

1.27

2.1%

Cl_alpha

0.085

0.0863

1.5%

L/D Max

39.1

39.1

0.0%

Alpha (L=0)

-.795

-0.8

0.4%

Cdo_min

0.0046

0.0043

6.8%

The above table shows close agreement of the MultiSurface results with experimental data. The following two graphs compare the results of MultiSurface Aerodynamics with the experiments in the report over a range of angles of attack. Again, the angle of attack results show good agreement with the experiments.


Cl vs. Angle of Attack


CD vs. CD

2D Airfoil Validation
MultiSurface Aerodynamics is equipped with a built-in airfoil analysis tool.  Click here to see the demo.  The follow are results for high and low reynolds numbers.

High Reynolds Number Comparisons
Comparisons were made with data taken form "Theory of WingSections" by Abbott et. al. The results below show excellent comparison with the data.


Comparison with Abbott & Von Donenhoff at Re=3M
Airfoil: NACA 0012
Circle-Experiment; Line- Software



Comparison with Abbott & Von Donenhoff at Re=3M
Airfoil: NACA 2412
Circle-Experiment; Line- Software



Comparison with Abbott & Von Donenhoff at Re=3M
Airfoil: NACA 4412
Circle-Experiment; Line- Software



Comparison with Abbott & Von Donenhoff at Re=3M
Airfoil: NACA 4412
Circle-Experiment; Line- Software


Low Reynolds Number Comparisons
We also compared the software with results obtained by Prof. Selig Aerodynamics group at the University Illinois Urbana Campus. The following results for relatively low Reynolds numbers also show excellent agreement with the experimental data.


Comparison with UIUC Data at Re=61K
Airfoil: SD7003
Circle-Experiment; Line- Software



Comparison with UIUC Data at Re=61K
Airfoil: SD7003
Circle-Experiment; Line- Software



Comparison with UIUC Data at Re=101K
Airfoil: SD7003
Circle-Experiment; Line- Software



Comparison with UIUC Data at Re=101K
Airfoil: SD7003
Circle-Experiment; Line- Software



Comparison with UIUC Data at Re=202K
Airfoil: SD7003
Circle-Experiment; Line- Software



Comparison with UIUC Data at Re=202K
Airfoil: SD7003
Circle-Experiment; Line- Software



Comparison with UIUC Data at Re=301K
Airfoil: SD7003
Circle-Experiment; Line- Software



Comparison with UIUC Data at Re=301K
Airfoil: SD7003
Circle-Experiment; Line- Software

Please click here for hydrofoil calculations.
Please click here to view Screen Shots of MultiSurface Aerodynamics.

How to Purchase
Please click here for more information.


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