By: MOHD NORIZZAT BIN ABDULLAH THANI DR NAZRI BIN NASIR
Transcript of By: MOHD NORIZZAT BIN ABDULLAH THANI DR NAZRI BIN NASIR
By:
MOHD NORIZZAT BIN ABDULLAH THANI
SX112706MMFO1
Supervised by:
DR NAZRI BIN NASIR
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Faculty of Mechanical Engineering (FKM)
OBJECTIVE
To quantify forces and vibration at the wing with winglet.
To know the performance of wing with winglet using UTM open wind tunnel testing.
To analyse the forces produce at different aircraft’s wings with pitch angle up to 40⁰.
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SCOPE
Literature review studied on the shapes, sizes and configuration of the winglets that have been used on flying aircraft.
The experiment will be executed at wind speed ranging from 10 to 20 m/s.( Until the vibration exist )
Design from Styrofoam and carrying payloads navigation as well as the existing electronic parts such as flight controller, battery and etc.
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WORK PLAN UGP 1
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No TaskWeek (UGP1)
1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17
1 RegistrationPlan
Actual
2 Problem Statement
Plan
Actual
3 Objective & Scope
Plan
Actual
4 Literature Review
Plan
Actual
5Research &
Methodology
Plan
Actual
6 Design & Analysis
Plan
Actual
7 PresentationPlan
Actual
Legend
Plan
Actual
METHODOLOGY FOR UGP 1
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DEFINE OBJECTIVE &
SCOPES
PROBLEM STATEMENT
LITERATURE REVIEW
RESEARCH & METHODOLOGY
DEFINE METHOD &
DESIGN
PRESENTATION & DRAFT
SUBMITTION
WORK PLAN UGP 2
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No Task
Week (UGP2)
1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16
1Design,Fabricate,Experimental
& Data Collection
Plan
Actual
2 Discussion
Plan
Actual
3 Conclusion/ Recommendation
Plan
Actual
4 Thesis Writing
Plan
Actual
METHODOLOGY FOR UGP 2
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Fabricated Wing
with Winglet
Installation of instruments
(PixRacer,
connector,battery and etc)
Installation of Wing in the
Wind TunnelOccurance of Vibration/
Flutter
Increase Wind SpeedCollect
data
Change the
Orientation of WingEnd
Literature Review on Winglet
Designs
NO
YES
Design & Simulation on
Winglet
CURRENT DESIGN & ANALYSIS
(UGP 1)
Simulations done by SolidWorks.
Flow type = Laminar and turbulent.
Velocity Parameters = 15 m/s.
Thermodynamic parameters = Applied.
Static Pressure = 101 kPa.
Material = High Impact Polystrene.
DETAILS ON DESIGN
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( AIRFOIL NACA 4412 )
PRESSURE DISTRIBUTION
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0 AOA 5 AOA 10 AOA
SIDE VIEW
PRESSURE DISTRIBUTION
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0 AOA 5 AOA 10 AOA
FRONT VIEW
PRESSURE DISTRIBUTION
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0 AOA 5 AOA 10 AOA
TOP VIEW
PRESSURE DISTRIBUTION
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0 AOA 5 AOA 10 AOA
ISOMETRIC VIEW
PRESSURE DISTRIBUTION
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0 AOA 5 AOA 10 AOA
SIDE VIEW
PRESSURE DISTRIBUTION
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FRONT VIEW
RESULTS
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101290
101295
101300
101305
101310
101315
101320
101325
101330
101335
101340
0 0.02 0.04 0.06 0.08 0.1
PRESSURE DISTRIBUTION LOWER WINGSPAN
0 AOA 10 AOA 5 AOAPressure ( Pa)
Length ( mm )
101280
101290
101300
101310
101320
101330
101340
0 0.02 0.04 0.06 0.08 0.1
PRESSURE DISTRIBUTION UPPER WINGSPAN
0 AOA 10 AOA 5 AOAPressure ( Pa)
Length ( mm )
RESULTS
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101280
101300
101320
101340
101360
101380
101400
101420
101440
0 0.02 0.04 0.06 0.08 0.1
PRESSURE DISTRIBUTION UPPER WINGSPAN
Winglet 0 AOA Winglet 10 AOA Winglet 5 AOA
Pressure ( Pa)
Length ( mm )
101280
101300
101320
101340
101360
101380
101400
101420
101440
101460
0 0.02 0.04 0.06 0.08 0.1
PRESSURE DISTRIBUTION LOWER WINGSPAN
Winglet 0 AOA Winglet 10 AOA Winglet 5 AOA
Pressure ( Pa)
Length ( mm )
RESULTS
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-0.15
-0.10
-0.05
0.00
0.05
0.10
0.15
0.20
0.25
0.30
0 . 0 0 0 . 0 2 0 . 0 4 0 . 0 6 0 . 0 8 0 . 1 0
COEFFICIENT OF PRESSURE
0 AOA Upper 0 AOA LowerCp
Length ( y/b )
-1.00
-0.80
-0.60
-0.40
-0.20
0.00
0.20
0.40
0 . 0 0 0 . 0 2 0 . 0 4 0 . 0 6 0 . 0 8 0 . 1 0
COEFFICIENT OF PRESSURE
0 AOA Upper 0 AOA LowerCp
Length ( y/b )
Without Winglet With Winglet
RESULTS
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Without Winglet With Winglet
-0.15
-0.10
-0.05
0.00
0.05
0.10
0.15
0.20
0.25
0.30
0 . 0 0 0 . 0 2 0 . 0 4 0 . 0 6 0 . 0 8 0 . 1 0
COEFFICIENT OF PRESSURE
5 AOA Upper 5 AOA Lower
Length ( y/b )
Cp
-0.60
-0.50
-0.40
-0.30
-0.20
-0.10
0.00
0.10
0.20
0.30
0 . 0 0 0 . 0 2 0 . 0 4 0 . 0 6 0 . 0 8 0 . 1 0
COEFFICIENT OF PRESSURE
5 AOA Upper 5 AOA LowerCp
Length ( y/b )
RESULTS
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Without Winglet With Winglet
-0.05
0.00
0.05
0.10
0.15
0.20
0.25
0.30
0.35
0 . 0 0 0 . 0 2 0 . 0 4 0 . 0 6 0 . 0 8 0 . 1 0
COEFFICIENT OF PRESSURE
10 AOA Upper 10 AOA LowerCp
Length ( y/b )
-0.60
-0.50
-0.40
-0.30
-0.20
-0.10
0.00
0.10
0.20
0.30
0 . 0 0 0 . 0 2 0 . 0 4 0 . 0 6 0 . 0 8 0 . 1 0
COEFFICIENT OF PRESSURE
10 AOA Upper 10 AOA LowerCp
Length ( y/b )
RESULTS & DISCUSSION
Without Winglet
• Pressure at lower wingspan is higher than upper.
• Lower wingspan-pressure are increase started at certain length.
• Upper wingspan-higher pressure at root and drop
With Winglet
• Pressure at lower and upper wingspan are almost same.
• High pressure started at root and drop.
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EXPERIMENTAL SETUP
FOR UGP 2
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1500
mm
3600mm
1500
mm
1500mm
Side View
Front View
Testing Section
WingWinglet
Clamping Area
PixRacer
Receiver
DAQ System
Specification• Pixracer V1.0 Flight.• Weight Pixracer: 21.08g• 36 x 36mm with 30.5 x
30.5mm hole grid with 3.2mm holes.
• MicroSD card reader, Micro USB.
• Power supply - 5-5.5VDC from USB.
REFERENCES1. Effect of winglets induced tip vortex structure on the performance of subsonic wings,
GauthamNarayan, BibinJohn,2016.
2. Design of Parametric Winglets and Wing tip devices – A Conceptual Design Approach, Saravanan Rajendran,2012.
3. An Experimental Study on the Effects ofWinglets on the Wake and Performance of a ModelWind Turbine, Nicolas Tobin , Ali M. Hamed and Leonardo P. Chamorro,2015.
4. The use of wing tip sails to reduce vortex drag, Aeronautical Journal, J. J. Spillman, 1978.
5. The Design and Testing of a Winglet Airfoil for Low-Speed Aircraft, AIAA,M. D. Maughmer, S. S. Tmothy, and S. M. Willits,2001.
6. http://airfoiltools.com/search/index?m%5Bgrp%5D=naca4d&m%5Bsort%5D=1
7. Experimental Investigation of theWake and the Wingtip Vortices of a UAV Model, Pericles Panagiotou, George Ioannidis ID , Ioannis Tzivinikos and Kyros Yakinthos,2017.
8. CFD SIMULATION STUDY OF AIR FLOW AROUND THE AIRFOIL USING THE MAGNUS EFFECT,Patryk SOKOŁOWSKI, Jacek CZARNIGOWSKI, Paweł MAGRYTA.
9. Force Measurement on Aircraft Model with and without Winglet using Low Speed Wind Tunnel, N.Muthusamy, S. Vignesh Kumar,Dr. C. Senthilkumar,2014.
10. Numerical simulation of aerodynamic performance for two dimensional wind turbine airfoils,JiYao, Weibin Yuan, jianliang Wang, JianbinXie, Haipeng Zhou, Mingjun Peng, YongSun, 2012.
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QUESTIONS
&
ANSWERS
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