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Transcript of (UNISIM(BEHAS)-Introduction to Aerospace)EAS105 -Lab3
Mohd Ashraf Mohd Ismail
Laboratory Experiment 3
Name : Mohammed Ashraf Bin Mohammed Ismail
Student No: N0806406
Contact No: 98225529
Date Submitted:
Lab. : Wind Tunnel Experiment
Course Instructor: Mr Roger Chua
2
Table of Contents
ABSTRACT .................................................................................................................. 3
INTRODUCTION ......................................................................................................... 4
OBJECTIVES................................................................................................................ 6
EXPIREMENT PROCEDURE ..................................................................................... 7
EXPIREMENT RESULT.............................................................................................. 9
Comparison between Theoretical and Experimental at 0° of flaps........................ 9
Comparison between 0° and 10° of flaps............................................................. 10
Comparison between 0°and 30° of flaps.............................................................. 11
DISCUSSION OF RESULT........................................................................................ 12
CONCLUSION............................................................................................................ 13
REFERENCE .............................................................................................................. 14
APPENDIX.................................................................................................................. 15
Introduction to Aerospace Engineering Lab 3
3
Abstract
In this experiment, we are out to show the relationship of the coefficient of lift and
drag in relation to the deployment of flaps (0, 10, 30). In addition to every change on
the angle of flaps, we also adjusted the angle of attack (AOA) (0,5,9,12,15,18) with
reference to the airflow. This show how it further affect the relationship how it affects
lift and drag. In this experiment we are using the aerofoil design of NACA 4412.
4
Introduction
Aircraft are supported in the air by an aerodynamic force called lift, which is
generated by the wings of the aircraft as air flows past the wings as a result of the
forward movement of the aircraft.
Many factor can affect the lift and drag component of the aerofoil which include
temperature, density, wing geometry, angle of attack(AOA) and angle of flaps
deployment and other factors. In this experiment we will concentrate on
Angle of Attack
Angle of Flaps Deployment - Flaps may be used to increase the maximum lift
coefficient, increase the wing area, or both. A change in the maximum lift coefficient
may be realized by a change in the shape of the airfoil section or by increased camber
Introduction to Aerospace Engineering Lab 3
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The Lift Coefficient and the Drag Coefficient represent the changes in lift and drag as
the angle of attack changes. CL and CD are not expressed by any physical unit, they
are rather absolute numbers obtained from either wind tunnel tests or derived
mathematically.
Lift and Drag Formulas
6
Objectives
From the experiment we were able to :
I. Show the relationship of Coefficient of lift and drag with varying the angle of
flaps deployment.
II. Show the relationship of Coefficient of lift and drag with varying the angle of
attack( AOA) within the same flap deployment angle
III. Compare and calculate the difference between the experimental value and the
theoretical value for the coefficient of lift and drag (only at clean flaps)
Introduction to Aerospace Engineering Lab 3
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Experimental Procedure
To observe, investigate and measure the lift and drag forces while varying the aerofoil
angle of attack, angle of flap and the test section velocity.
The type of aerofoil selected for the following experiment is NACA 4412 camber
aerofoil(Figure 1).
Figure 1
- Aerofoil Span b 300mm
- Aerofoil Chord length 100mm
- Average Sea level Temperature 23 ° c
- Average Sea level Pressure 1013mbar
- Velocity of airflow 16.9 m/s
- Air Density 1.19 kg/m³
8
Procedure:
1. Mount the aerofoil on the test section of the wind tunnel( figure 2).
2. Adjust the angle of flaps deployment first.
3. Adjust the Angle of attack (AOA) and then tighten he set screw with the Allen
wrench.
4. Monitor the Lift the Drag vales on the computer.
5. Repeat step 3 until the readings for all different angle of attack for that
particular flap deployment has been taken down.
6. Then repeat step 2 to adjust the angle of flaps deployment
7. Record and tabulate the result in a table form.
Figure 2
Introduction to Aerospace Engineering Lab 3
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Experiment Result
Comparison between theoretical and experimental values at 0° flaps deployment
10
Comparison between 10° and 0° of flap deployment
Introduction to Aerospace Engineering Lab 3
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Comparison between 30° and 0° of flap deployment
12
Discussion of Result
For the 1st lab comparison between the experimental value and the theoretical values(Both 0° flaps), the % error is quite big partly because NACA uses 54 pressure points and uses a 24’’ chord length to test on their aerofoil 4412 different from sample aerofoil. Another issue is that the environmental variable such as air pressure, air density, sea level temperature and velocity air speed are not the same. Other possible errors may be due to improper setup of experiment and the fluctuating airspeed readings
For the 2nd lab comparison between flaps deployment of 0° and 10°, the values are almost similar but at 10° flaps, the aerofoil starts to gain more lift at low AOA(0°-4°) but also loses lift faster at it’s stall angle(12°). For both value for drag the values are very similar
For the 3rd lab comparison between flaps deployment of 0° degrees and 30°, the difference are more distinct. At lower AOA airflow over the 30° flaps gain much more lift. The Cl values are in fact more that 2 times than clean flaps. The Cd is also slightly more than the clean flaps. At 30° flaps aerofoil start to stall at a much lower AOA compared to 0° flaps. The Cl starts to loses lift at 9° and the Cd starts to increase exponentially also at 9°.
I have a better understanding of lift and drag and finding the most optimum condition and applying it to the different phase in flying.
Take Off – Most aircraft would take off with Flaps 10° as it will give them the max lift and therefore BEST Climb Rate. It will also reduce the length of runway needed.
Cruising – At cruising you don’t need to climb but just to have the best something ratio. It you look properly at clearer research, the greatest difference between lift and drag is when aircraft is at AOA of 4° and no flaps. That’s why most aircraft wings are rigged at an angle of 4° (Angle of Incident). It has the least drag therefore aerodynamically it’s the most efficient condition to cruise.
Landing – At landing aircraft most aircraft want to descend gradually and land as slowly as possible (landing speed). Therefore we need more drag than lift but not till aircraft is stalled. Most of the time full flaps either 30 or 40° is being used for landing phase
Introduction to Aerospace Engineering Lab 3
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Conclusion The experiment shows the relationship of lift and drag is affected by adjusting the angle of attack, angle of flaps deployment or even both. By completing the experiment
To sum it all up:
1) Different AOA for same flaps deployment:
a) Increase in AOA will result in higher lift than lower AOA but only before
stalling angle. Upon exceeding stalling angle, lift will decrease drastically
b) Drag will remain quite constant, only increasing slightly with increase in
AOA. Upon exceeding stalling angle, it will increase exponentially.
2) Different AOA at different flaps deployment:
a) Increase in lift initially with more deployment of angle of flaps. As same AOA
more lift will be generated with more deflection in flaps.
b) More angle of flaps will result in slightly increase in drag because of the
deflection in shape.
c) More angle of flaps will result the stalling angle to occur at lower AOA.
14
Reference 1. http://pilotsweb.com/principle/liftdrag.htm
2. http://classicairshows.com/Education/Aerodynamics/BernoulliAT1243
.htm
3. http://acam.ednet.ns.ca/curriculum/wing.htm
4. http://www.tpub.com/content/nasa1996/NASA-96-jcp-wka/NASA-96-
jcp-wka0009.htm
5. Theory of the Wing Section by IRA H.Abbot and Albert E. Von
Doenhoff. Published by Dover Publication. 1st publication in 1959
6. http://www.aerolab.com/
7.
Introduction to Aerospace Engineering Lab 3
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Appendix I http://www.google.com/imgres?imgurl=http://mshades.free.fr/flapping/Cx4412.jpg&imgrefurl=http://
mshades.free.fr/flapping/selfincidentwingsection.html&h=557&w=324&sz=58&tbnid=DinGwPpi10U
J::&tbnh=133&tbnw=77&prev=/images%3Fq%3Dpicture%2Bof%2BNaca%2B4412&usg=__3dsax-
vRhkwdahNJ86899t8_3pE=&sa=X&oi=image_result&resnum=1&ct=image&cd=1
16
Introduction to Aerospace Engineering Lab 3
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NACA 4412 (Stations and ordinates given in per cent of airfoil chord)
Upper Surface Lower Surface Station Ordinate Station Ordinate
0.0000 0.0000 0.0000 0.0000 0.5000 1.6549 0.5000 -0.8857 0.7500 1.9551 0.7500 -1.1096 1.2500 2.4478 1.2500 -1.4338 2.5000 3.3829 2.5000 -1.9484 5.0000 4.7302 5.0000 -2.4834 7.5000 5.7597 7.5000 -2.7429
10.0000 6.5986 10.0000 -2.8638 15.0000 7.8878 15.0000 -2.8791 20.0000 8.7963 20.0000 -2.7320 25.0000 9.4055 25.0000 -2.5089 30.0000 9.7589 30.0000 -2.2595 35.0000 9.8849 35.0000 -2.0162 40.0000 9.8030 40.0000 -1.8030 45.0000 9.5563 45.0000 -1.6058 50.0000 9.1916 50.0000 -1.3990 55.0000 8.7174 55.0000 -1.1930 60.0000 8.1404 60.0000 -0.9955 65.0000 7.4644 65.0000 -0.8124 70.0000 6.6958 70.0000 -0.6483 75.0000 5.8340 75.0000 -0.5054 80.0000 4.8817 80.0000 -0.3855 85.0000 3.8369 85.0000 -0.2888 90.0000 2.7001 90.0000 -0.2146 95.0000 1.4642 95.0000 -0.1609
100.0000 0.1302 100.0000 -0.1248 L.E. radius = 1.587 percent c slope of mean line at LE = 0.2000
18
NACA 4412 (Stations and ordinates given in per cent of airfoil chord)
Upper Surface Lower Surface Station Ordinate Station Ordinate
0.0000 0.0000 0.0000 0.0000 0.2634 1.2975 0.7366 -1.0988 0.4641 1.6057 1.0359 -1.3085 0.8898 2.1054 1.6102 -1.6132 2.0181 3.0543 2.9819 -2.0856 4.3872 4.4390 5.6128 -2.5640 6.8264 5.5049 8.1736 -2.7862 9.3054 6.3810 10.6946 -2.8810
14.3370 7.7414 15.6630 -2.8664 19.4291 8.7091 20.5709 -2.7091 24.5557 9.3621 25.4443 -2.4871 29.7003 9.7442 30.2997 -2.2442 34.8513 9.8843 35.1487 -2.0093 40.0000 9.8030 40.0000 -1.8030 45.0620 9.5526 44.9380 -1.6082 50.1176 9.1816 49.8824 -1.4038 55.1650 8.6997 54.8350 -1.1997 60.2026 8.1144 59.7974 -1.0033 65.2292 7.4317 64.7708 -0.8206 70.2437 6.6558 69.7563 -0.6558 75.2451 5.7897 74.7549 -0.5119 80.2323 4.8350 79.7678 -0.3906 85.2042 3.7924 84.7958 -0.2924 90.1599 2.6611 89.8401 -0.2166 95.0979 1.4395 94.9021 -0.1617
100.0167 0.1249 99.9833 -0.1249 L.E. radius = 1.587 percent c slope of mean line at LE = 0.2000 http://www.pdas.com/sections45.htm#4412
Introduction to Aerospace Engineering Lab 3
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Aluminum Alloy 5052
Available
Shapes
Typical
Chemistry
Characteristcs
Typical
Applications
Mechanical
Properties
Fabrication Guide
Available Shapes
5052 is available in Coil, Plate and Sheet.
- Top -
Typical Chemistry (% Maximum unless shown as a range)
Cu Si + Fe Mn Mg Zn Cr Al
0.10 0.45 0.10 2.2 / 2.8 0.10 0.15 / 0.35 Balance
- Top -
Characteristics
5052 is one of the higher strength non-heat-treatable alloys. It has a high fatigue strength and is a good choice for structures subjected to excessive vibration. The alloy has excellent corrosion resistance, particularly in marine atmospheres. The formability of the grade is excellent and in the annealed condition it offers higher strengths than 1100 or 3003 grades.
- Top -
Typical Applications
20
5052 is often used in high strength sheet metal work, marine components, appliances, fuel and oil tubing.
- Top -
Mechanical Properties
Tensile Strength Yield Strength
Elongation
Brinell Hardness
ksi MPa ksi MPa % in 2" (50mm)
5052-0 28.0 196 13.0 91 25 47
5052-H32 33.0 231 28.0 196 12 60
5052-H34 38.0 266 31.0 217 10 68
- Top -
Fabrication Guide
Weldability
Corrosion
Resistance
Formability
Machinability Mpa TIG Resist.
5052-0 A A D A A B
5052- A B C A A A
Introduction to Aerospace Engineering Lab 3
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H14
5052-H18
A B C A A A
Aluminum 2024-O
Subcategory: 2000 Series Aluminum Alloy; Aluminum Alloy; Metal; Nonferrous
Metal
Close Analogs:
Composition Notes:
A Zr + Ti limit of 0.20 percent maximum may be used with this alloy designation for
extruded and forged products only, but only when the supplier or producer and the
purchaser have mutually so agreed. Agreement may be indicated, for example, by
reference to a standard, by letter, by order note, or other means which allow the Zr +
Ti limit.
Aluminum content reported is calculated as remainder.
Composition information provided by the Aluminum Association and is not for
design.
Key Words: Aluminium 2024-O; UNS A92024; ISO AlCu4Mg1; NF A-U4G1
(France); DIN AlCuMg2; AA2024-O, ASME SB211; CSA CG42 (Canada)
Component Wt. %
Al 90.7 - 94.7
Cr Max 0.1
Cu 3.8 - 4.9
Fe Max 0.5
Component Wt. %
22
Mg 1.2 - 1.8
Mn 0.3 - 0.9
Other, each Max 0.05
Other, total Max 0.15
Component Wt. %
Si Max 0.5
Ti Max 0.15
Zn Max 0.25
Material Notes:
General 2024 characteristics and uses (from Alcoa): Good machinability and surface
finish capabilities. A high strength material of adequate workability. Has largely
superceded 2017 for structural applications. Use of 2024-O not recommended unless
subsequently heat treated.
Uses: Aircraft fittings, gears and shafts, bolts, clock parts, computer parts, couplings,
fuse parts, hydraulic valve bodies, missile parts, munitions, nuts, pistons, rectifier
parts, worm gears, fastening devices, veterinary and orthopedic equipment, structures.
Data points with the AA note have been provided by the Aluminum Association, Inc.
and are NOT FOR DESIGN.
Physical Properties Metric English Comments
Density 2.78 g/cc 0.1 lb/in³ AA; Typical
Mechanical Properties
Hardness, Brinell 47 47 AA; Typical; 500 g load; 10 mm ball
Ultimate Tensile Strength 186 MPa 27000 psi AA; Typical
Tensile Yield Strength 75.8 MPa 11000 psi AA; Typical
Elongation at Break 20 % 20 % AA; Typical; 1/16 in. (1.6 mm) Thickness
Elongation at Break 22 % 22 % AA; Typical; 1/2 in. (12.7 mm) Diameter
Introduction to Aerospace Engineering Lab 3
23
Modulus of Elasticity 73.1 GPa 10600 ksi AA; Typical; Average of tension
and compression. Compression modulus is about 2% greater than tensile modulus.
Ultimate Bearing Strength 345 MPa 50000 psi Edge distance/pin
diameter = 2.0
Bearing Yield Strength 131 MPa 19000 psi Edge distance/pin
diameter = 2.0
Poisson's Ratio 0.33 0.33
Fatigue Strength 89.6 MPa 13000 psi AA; 500,000,000 cycles
completely reversed stress; RR Moore machine/specimen
Machinability 30 % 30 % 0-100 Scale of Aluminum Alloys
Shear Modulus 28 GPa 4060 ksi
Shear Strength 124 MPa 18000 psi AA; Typical
Electrical Properties
Electrical Resistivity 3.49e-006 ohm-cm 3.49e-006 ohm-cm AA; Typical at
68°F
Thermal Properties
CTE, linear 68°F 23.2 µm/m-°C 12.9 µin/in-°F AA; Typical; Average over 68-
212°F range.
CTE, linear 250°C 24.7 µm/m-°C 13.7 µin/in-°F Average over the range 20-
300ºC
Specific Heat Capacity 0.875 J/g-°C 0.209 BTU/lb-°F
Thermal Conductivity 193 W/m-K 1340 BTU-in/hr-ft²-°F AA; Typical at
77°F
Melting Point 502 - 638 °C 935 - 1180 °F AA; Typical range based on typical
composition for wrought products 1/4 inch thickness or greater. Eutectic melting is
not eliminated by homogenization.
Solidus 502 °C 935 °F AA; Typical
Liquidus 638 °C 1180 °F AA; Typical
24
Processing Properties
Annealing Temperature 413 °C 775 °F
Solution Temperature 256 °C 493 °F
Aluminum 5052-O
Subcategory: 5000 Series Aluminum Alloy; Aluminum Alloy; Metal; Nonferrous
Metal
Close Analogs:
Composition Notes:
Aluminum content reported is calculated as remainder.
Composition information provided by the Aluminum Association and is not for
design.
Key Words: UNS A95052; ISO AlMg2.5; Aluminium 5052-O; AA5052-O
Component Wt. %
Al 95.7 - 97.7
Cr 0.15 - 0.35
Cu Max 0.1
Fe Max 0.4
Component Wt. %
Mg 2.2 - 2.8
Mn Max 0.1
Other, each Max 0.05
Component Wt. %
Introduction to Aerospace Engineering Lab 3
25
Other, total Max 0.15
Si Max 0.25
Zn Max 0.1
Material Notes:
Data points with the AA note have been provided by the Aluminum Association, Inc.
and are NOT FOR DESIGN.
Physical Properties Metric English Comments
Density 2.68 g/cc 0.0968 lb/in³ AA; Typical
Mechanical Properties
Hardness, Brinell 47 47 AA; Typical; 500 g load; 10 mm ball
Ultimate Tensile Strength 193 MPa 28000 psi AA; Typical
Tensile Yield Strength 89.6 MPa 13000 psi AA; Typical
Elongation at Break 25 % 25 % AA; Typical; 1/16 in. (1.6 mm) Thickness
Elongation at Break 30 % 30 % AA; Typical; 1/2 in. (12.7 mm) Diameter
Modulus of Elasticity 70.3 GPa 10200 ksi AA; Typical; Average of tension
and compression. Compression modulus is about 2% greater than tensile modulus.
Ultimate Bearing Strength 345 MPa 50000 psi Edge distance/pin
diameter = 2.0
Bearing Yield Strength 131 MPa 19000 psi Edge distance/pin
diameter = 2.0
Poisson's Ratio 0.33 0.33
Fatigue Strength 110 MPa 16000 psi AA; 500,000,000 cycles
completely reversed stress; RR Moore machine/specimen
Machinability 30 % 30 % 0-100 Scale of Aluminum Alloys
Shear Modulus 25.9 GPa 3760 ksi
Shear Strength 124 MPa 18000 psi AA; Typical
Electrical Properties
26
Electrical Resistivity 4.99e-006 ohm-cm 4.99e-006 ohm-cm AA; Typical at
68°F
Thermal Properties
CTE, linear 68°F 23.8 µm/m-°C 13.2 µin/in-°F AA; Typical; Average over 68-
212°F range.
CTE, linear 250°C 25.7 µm/m-°C 14.3 µin/in-°F Average over the range 20-
300ºC
Specific Heat Capacity 0.88 J/g-°C 0.21 BTU/lb-°F Estimated from
trends in similar Al alloys.
Thermal Conductivity 138 W/m-K 960 BTU-in/hr-ft²-°F AA; Typical at 77°F
Melting Point 607 - 649 °C 1125 - 1200 °F AA; Typical range based on
typical composition for wrought products 1/4 inch thickness or greater
Solidus 607 °C 1125 °F AA; Typical
Liquidus 649 °C 1200 °F AA; Typical
Processing Properties
Annealing Temperature 343 °C 650 °F holding at temperature not required
Hot-Working Temperature 260 - 510 °C 500 - 950 °F
Introduction to Aerospace Engineering Lab 3
27
Aluminum 7075-O
Subcategory: 7000 Series Aluminum Alloy; Aluminum Alloy; Metal; Nonferrous
Metal
Close Analogs:
Composition Notes:
A Zr + Ti limit of 0.25 percent maximum may be used with this alloy designation for
extruded and forged products only, but only when the supplier or producer and the
purchaser have mutually so agreed. Agreement may be indicated, for example, by
reference to a standard, by letter, by order note, or other means which allow the Zr +
Ti limit.
Aluminum content reported is calculated as remainder.
Composition information provided by the Aluminum Association and is not for
design.
Key Words: UNS A97075; ISO AlZn5.5MgCu(A); Aluminium 7075-O; AA7075-O
Component Wt. %
Al 87.1 - 91.4
Cr 0.18 - 0.28
Cu 1.2 - 2
Fe Max 0.5
Component Wt. %
Mg 2.1 - 2.9
Mn Max 0.3
Other, each Max 0.05
Other, total Max 0.15
28
Component Wt. %
Si Max 0.4
Ti Max 0.2
Zn 5.1 - 6.1
Material Notes:
General 7075 characteristics and uses (from Alcoa): Very high strength material used
for highly stressed structural parts. The T7351 temper offers improved stress-
corrosion cracking resistance.
Uses: Aircraft fittings, gears and shafts, fuse parts, meter shafts and gears, missile
parts, regulating valve parts, worm gears, keys, aircraft, aerospace and defense
applications.
Data points with the AA note have been provided by the Aluminum Association, Inc.
and are NOT FOR DESIGN.
Physical Properties Metric English Comments
Density 2.81 g/cc 0.102 lb/in³ AA; Typical
Mechanical Properties
Hardness, Brinell 60 60 AA; Typical; 500 g load; 10 mm ball
Hardness, Knoop 80 80 Converted from Brinell Hardness Value
Hardness, Vickers 68 68 Converted from Brinell Hardness Value
Ultimate Tensile Strength 228 MPa 33000 psi AA; Typical
Tensile Yield Strength 103 MPa 15000 psi AA; Typical
Elongation at Break 16 % 16 % AA; Typical; 1/2 in. (12.7 mm) Diameter
Elongation at Break 17 % 17 % AA; Typical; 1/16 in. (1.6 mm) Thickness
Modulus of Elasticity 71.7 GPa 10400 ksi AA; Typical; Average of tension
and compression. Compression modulus is about 2% greater than tensile modulus.
Poisson's Ratio 0.33 0.33
Shear Modulus 26.9 GPa 3900 ksi
Introduction to Aerospace Engineering Lab 3
29
Shear Strength 152 MPa 22000 psi AA; Typical
Electrical Properties
Electrical Resistivity 3.8e-006 ohm-cm 3.8e-006 ohm-cm
Thermal Properties
CTE, linear 68°F 23.6 µm/m-°C 13.1 µin/in-°F AA; Typical; Average over 68-
212°F range.
CTE, linear 250°C 25.2 µm/m-°C 14 µin/in-°F Average over the range 20-
300ºC
Specific Heat Capacity 0.96 J/g-°C 0.229 BTU/lb-°F
Thermal Conductivity 173 W/m-K 1200 BTU-in/hr-ft²-°F
Melting Point 477 - 635 °C 890 - 1175 °F AA; Typical range based on typical
composition for wrought products 1/4 inch thickness or greater. Homogenization may
raise eutectic melting temperature 20-40°F but usually does not eliminate eutectic
melting.
Solidus 477 °C 890 °F AA; Typical
Liquidus 635 °C 1175 °F AA; Typical
Processing Properties
Annealing Temperature 413 °C 775 °F
Solution Temperature 466 - 482 °C 870 - 900 °F