By:

MOHD NORIZZAT BIN ABDULLAH THANI

SX112706MMFO1

Supervised by:

DR NAZRI BIN NASIR

1

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.

2

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.

3

WORK PLAN UGP 1

4

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

5

DEFINE OBJECTIVE &

SCOPES

PROBLEM STATEMENT

LITERATURE REVIEW

RESEARCH & METHODOLOGY

DEFINE METHOD &

DESIGN

PRESENTATION & DRAFT

SUBMITTION

WORK PLAN UGP 2

6

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

7

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

9

( AIRFOIL NACA 4412 )

PRESSURE DISTRIBUTION

10

0 AOA 5 AOA 10 AOA

SIDE VIEW

PRESSURE DISTRIBUTION

11

0 AOA 5 AOA 10 AOA

FRONT VIEW

PRESSURE DISTRIBUTION

12

0 AOA 5 AOA 10 AOA

TOP VIEW

PRESSURE DISTRIBUTION

13

0 AOA 5 AOA 10 AOA

ISOMETRIC VIEW

PRESSURE DISTRIBUTION

14

0 AOA 5 AOA 10 AOA

SIDE VIEW

PRESSURE DISTRIBUTION

15

FRONT VIEW

RESULTS

16

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

17

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

18

-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

19

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

20

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.

21

EXPERIMENTAL SETUP

FOR UGP 2

22

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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