Transcript Aerodynamic Shape Design Optimization of Winglets

Gianluca Minnella
Yuniesky Rodriguez
Jose Ugas

Design, construction and
testing of an optimal
winglet configuration.
Dr. George Dulikravich



De-strengthening of tip
vortices
Additional positive-traction
component
INCREASED FUEL EFFICIENCY


INCREASED PAYLOAD
CAPABILITIES
Improved load
distribution over
wing-span

Wingtip Fence

Blended
Elliptical
Winglet

Blended Winglet






Attainment of modified-desired Cp
distribution: CFD
Inverse shape design: MGM Fourier Series
Optimization: Particle Swarm Algorithm
Removal of interferences: CFD
Manufacturing: High p-plastics, Metal-Alloy
Testing: Surface p-distribution at varying
angles of attack


CFD – surface p-distribution
Theory of Flow Separation – flow separation
point will be moved toward Trailing Edge
◦ DESIRED PRESSURE DISTRIBUTION


Airfoil will be
designed specifically
for chosen flow.
Only Cp data is
needed to generate
airfoil.

o
o
MGM
Elastic membrane.
Mass-damperspring system.

o
o
Fourier Adaptation
Faster conversion.
Iterations- until
desired pressure
distribution is met.
Increase design quality
Minimize time and computer costs
•
•

S = {Xi}
with
i=1,2,3…n
Particle-Swarm



Yi is compared to its
actual performance
and set to a better
performance. (7.2)
The general best
solution is updated to
the position with the
best performance
within the swarm. (7.3)
Now the particles
velocity and position
are updated separately
for each dimension j.
(7.4, 7.5)

Construct a FORTRAN code interconnected to
AnSys to obtain OPTIMAL SHAPE

2 Alternatives :
◦ DEEP DRAWN – 2 half shells, Laser Weld, AISI 304
◦ CAST – Metal Alloy, Hi-p plastics
Both alternatives require the commission of
molding/casting tools

Surface Pressure Distribution

Flow Separation Point

o
o

o
o

o
o
Gianluca
Computational Analysis
Manufacturing
Jose
Inverse Shape Design
Manufacturing
Yuniesky
Optimization
Manufacturing


Thanks to winglets, aircrafts will be able to:
◦ Consume less fuel
◦ Extend range capabilities
◦ Reduce takeoff distance
◦ Reduce noise emissions
◦ Increase payload
◦ Increase Aerodynamic efficiency
◦ Increase L/D Ratio
Working with 2-D version of Fourier Adaptation, to
follow up with 3-D version.