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
. 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.
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
