09 AE2258 Aerodynamics Lab Manual

8/12/2019 09 AE2258 Aerodynamics Lab Manual

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RAJALAKSHMI ENGINEERING COLEGE, CHENNAI

B.E. AERONAUTICAL ENGINEERING

SEMESTER-IV

AE 2258 AERODYNAMICS LABORATORY

REGULATION 2008

OBJECTIVE:

To familiarize students in basic aerodynamics and the use of wind tunnels.

LIST OF EXPERIMENTS

1. Introduction low speed wind tunnel

2. Flow visualization in water flow channel

3. Flow visualization using smoke generator

4. Plot of RPM Vs test section velocity in a subsonic wind tunnel.

5. Study of lift characteristics on symmetric aerofoil, cambered aerofoil and bluff

bodies

6. Pressure distribution over rough and smooth circular cylinder

7. Pressure distribution over symmetric and cambered airfoil and estimation of CLand CD.

8. Study of Calibration of Supersonic wind tunnel.

9. Velocity distribution in nozzle using supersonic free jet

10.Flow visualization using Shadowgraph system

AUGMENTED EXPERIMENT

1. Pressure distribution over wedge airfoil and estimation of CLand CD

2. Mini Project


2/26

EXP.NO: - 1 LOW SPEED WIND TUNNEL

AimTo study in details about the low speed wind tunnel.

Introduction:

The information useful for solving aerodynamic problems of aeronautical,space, automobile, and civil engineering structures are best obtained rapidly,

economically and accurately by testing the scale models and sometimes actual structures

in wind tunnel. The size, speed and other environmental conditions of the tunnel are

determined by the actual under problems. Leaving the size and environmental conditionsto the actual users, the speed determines the type of the tunnel namely subsonic (low

speed), near sonic, transonic, supersonic and hypersonic. While the speed of these tunnels

is obviously named with the reference to the sonic (sound) velocity, the low speed tunnelwhich is our concern is below 300mph. an alternative definition to the low speed tunnel

would be the tunnel where the compressibility of air is negligible.

Specifications:

Type of tunnel : Subsonic Suction Type

Test section : 300mm 300mm 500mm (Length)Air speed : Upto 50m/s

Contraction ratio : 9:1

Overall size : 1.2m 2.2m 7.0mPower required : AC 3 phase, 440 volts, 14A

Drive : Axial flow fan driven variable speed DC Motorwith Thyristor Controller

Main parts:

Honey comb inlet mesh screen, effuser, diffuser, blower unit with DC motor,

lift/drag balance, multitube manometer, smoke generator, pitot tube and transversemechanism, digital lift/drag indicators.

Preparation:

Tunnel balance is a two-component type designed using electrical strain gauge toindicate lift and drag forces on digital lift and drag indicator in kg and Newton. Balance

is intended to indicate lift and drag incase of aerofoils and drag force in case of bluffbodies. Example: spherical, hemispherical, round disc and automobile models. These

models are put on the string.

Before the model is put on the string air is blown and it is necessary to calibratebalance along with digital meters. For the purpose, a calibration jig is provided with a set

of weights.


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Fix calibration jigs and to the top of the test section with the help of wing nuts.

Fix dummy rod to string and see that the top dummy rod is at the centre of test section.Now pass the wire around the dummy rod and hang it to the weights.

Switch on the strain indicator and observe the reading on it be zero. If reading are

not same after weights are added use CAL knob to obtain the correct reading. Remove

the calibration jig dummy rod and fix the model and run the tunnel for studying varioustypes of experiments.

Operating instructions:

All the components mentioned are integrated for conducting various experiments.

Follow the instructions given below.1. Connect the power card to the 400v,30A,3PH AC power supply with neutral

and earth connections.

2. Keep the speed controller knob at 03. Check all the switches of the controller are in OFF position before starting

4.

Put on the mains and observe the main indicator. Lights are ON at the bottomof the control panel

5. Now switch on the control and observe the console light is ON6. Select particular experiment and fix the requirement model in the test section

7. Follow the instruction for preparation and operation of different attachments

accessories explained in earlier pages.8. Observe that no tools or loose parts are left in the test section and then close

the transparent window.

9. Now increase the speed control knobs slowly in the clockwise direction andobserve vthe DC motor picking up the speed gradually.

10.Observe the movement of manometer liquid in inclined manometer(velocityindicator). Set the requirement valve of air velocity by adjusting the knob on

DC drive.

11.Take readings in the respective experiments detailed.12.While stopping, gradually decrease the speed and then switch of the DC motor

controller.

Note:

1. Do not clean the transparent test section windows with petrol, kerosene orother chemical detergents. Use only the light soap water.

2. Check the electrical installation property before switching it ON.

3. Do not bring any fire near the smoke generator during the flow visualizationexperiment.


4/26

EXP NO: - 2FLOW VISUALIZATION IN WATER FLOW CHANNEL

Aim:-

To visualize the flow over two dimensional objects using water flow channel.

Apparatus required:

Water flow channel, various shapes (cylinder, airfoil and square).

Description:The water flow channel is a device used to visualize the 2D flow past an object.

The channel consists of a test section proceeded by contraction. This contraction

increases the test section speed and renders the flow stream lined and uni-directional. The

corner valves in the return circuit provide a smooth entry of water into the contraction.The entire set up is arranged in a shallow rectangular box like tank filled with water to a

required height. The flow in the test section established by means of two sets of parallel

discs rotating in opposite direction which is immersed in water. The water is re-circulatedso that the system can work continuously. A half HP AC motor through a belt pulley

drives arrangement, which drives at a lower speed. The speed of the stream is kept low so

as to avoid turbulence and ripple formation on the water surface.

Procedure:

Two-dimensional models are kept in the test section and the flow pattern aroundthese models is made visible by sprinkling aluminum powder. The water channel is well

situated for the study of real flow around two dimensional objects. This type of flow

visualization technique is used to study the effect of the shape model on the flow pattern

when kept in a streamlined flow. The following models are used for flow visualization.

a) Circular cylinder

b) Square prismc) Symmetric aerofoil

Result:

Thus, the flow over the two dimensional objects has been visualized using the water flowchannel.


5/26

EXP NO:-3 FLOW VISUALIZATION USING SMOKE GENERATOR

Aim:-To study the flow visualization technique by smoke generation.

Apparatus required:-

Subsonic wind tunnel, Smoke generator, Liquid paraffin, Any Aerodynamicmodel

Procedure:-

1. Check all the connections of the tubes.

2. Pour liquid into the reservoir, so that half of it is filled.3. Then raise the wire of the reservoir such that the liquid level in the water tank of

the smoke generator is above some mm below the nozzle of the outlet.

4. Connect the heater with the heater control which is a 400W controller.5. Keep the controller in the minimum and switch on the power to the heater using

the function knob.

6. Slowly increase the heating up to 3/4th of the capacity.

7. Observe the liquid paraffin which will start flowing wider.8. The liquid level rises in the tube with the bubbles of liquid paraffin start reaching

the nozzle exit.

9. At this point of time turn on the blower to send the pressurized air. The cold airmix with oil and forms dense smoke.

10.By controlling the heating and the liquid level in the tube, a good dense white

smoke can be generated.

Result:-

Thus, the flow visualization technique is studied by generating smoke.


6/26

EXP NO:-4 PLOT OF RPM VS TEST SECTION VELOCITY IN A SUBSONIC

WIND TUNNEL

Aim

To estimate the test section speed characteristics of the subsonic wind tunnel withrespect to the rpm of the drive motor.

Apparatus Required

Subsonic Wind tunnel, Pitot tube

Procedure:

All the components mentioned are integrated for conducting various experiments.

Follow the instructions given below.

1. Connect the power card to the 400v, 30A, 3PH AC power supply with neutral andearth connections.

2. Keep the speed controller knob at 0.3. Check all the switches of the controller are in OFF position before starting.

4. Put on the mains and observe the main indicator. Lights are ON at the bottom of

the control panel.

5. Now switch on the control and observe the console light is ON.6. Select particular experiment and fix the requirement model in the test section.

7. Follow the instruction for preparation and operation of different attachments

accessories explained in earlier pages.8. Observe that no tools or loose parts are left in the test section and then close the

transparent window.9. Now increase the speed control knobs slowly in the meter and observe the AC

motor picking up the speed gradually.

10. Observe the movement of methanol liquid in inclined manometer (velocity

indicator).

11. Take readings in the respective experiments detailed.12. While stopping, gradually decrease the speed and then switch of the AC motor

controller.


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Tabulation:

Graph:

A graph between rpm and velocity has to be plotted.

RPM

Result:-

Hence the test section speed characteristics of the subsonic wind tunnel with respect to

the rpm are estimated and it shows that there is a linear variation of velocity with respect

to the variation of RPM.

0

5

10

15

20

25

30

35

40

45

0 200 400 600 800 1000 1200

RPMVsVelocity

RPMVsVelocity

S.NO. RPMV = 3.62h

m/s

1 200 7.1

2 400 15.1

3 600 23.6

4 800 30.8

5 1000 38.8


8/26

EXP NO: - 5 STUDY OF LIFT& DRAG CHARACTERISTICS OF

SYMMETRIC, CAMBERED AEROFOIL AND BLUFF BODIES

Aim:

To study the lift/drag characteristics on symmetrical aerofoil, cambered aerofoil

and bluff bodies

Apparatus required:

1) Low speed wind tunnel

2) Symmetric aerofoil model

3) Cambered aerofoil4) Bluff body

Formula Used:

Lift Coefficient

SV

LC

L

2

2

1

Drag Coefficient

SV

DC

D

2

2

1

L = Lift in ND = Drag in N

= Density of air in kg/m3V = Velocity in m

3/s

S = Wetted area in m2

Procedure:

a) Prepare a wind tunnel and calibrate it with the lift drag balance and ensure it isfully serviceable.

b) The operating instructions are to be meticulously followed.c) Fix the model on the vertical string and lock it.d) Close the test section and ensure that no items are left inside the test section

before closing.

e) Blank all the points.f) Set the lift force indicator to zero.

g) Fix the required air velocity using the velocity indicator.


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h) Now by changing the angle of attack the corresponding lift force is noted

down.i) The same is repeated for different angle of attacks.

TABULAR COLUMN

Sl.No.Angle of

attack ()L D CL CD

Graph: aerofoil (symmetric and cambered)

1) Coefficients of lift Vs angle of attack.

2) Coefficient of drag Vs angle of attack.3) CDVs CL.

1

0.8

0.60.4

0.2

0

0.2

0.4

0.6

0.8

30 20 10 0 10 20 30

CL

CD


10/26

Graph: (bluff body)

4) Coefficients of lift Vs angle of attack.

5) Coefficient of drag Vs angle of attack.

6) CDVs CL.

Result:

Thus, the characteristics of symmetrical, cambered airfoil and bluff bodies were

studied and the graphs are plotted between CLand .

0.4

0.2

0

0.2

0.4

0.6

0.8

1

1.2

20 10 0 10 20 30

CL

CD


11/26

EXP NO: - 6 PRESSURE DISTRIBUTION OVER ROUGH AND

SMOOTH CIRCULAR CYLINDER

Aim:-

To study the pressure distribution over rough and smooth circular cylinders.

Apparatus:-

1) Low speed wind tunnel2) Multi-tube Manometer

3) Smooth and rough circular Cylinder model

Formulas used:-

Coefficient of pressure at port number x is given by:

Cpx= (p- px) / (p0- p) = (px- p) / q

Note: po= p+ (1/ 2) V2

po- p= (1/ 2) V2= q

Procedure:-

1. Prepare the low speed wind tunnel as per the instruction for the pressure

distribution.2. Ensure proper electrical installation and other safety.

3. Ensure proper and adequate power supply.

4. Fix the cylinder in the test section over which the pressure distribution is to bestudied.

5. Connect the tubes bundle from multitube manometer to the corresponding

tubes in the cylinder model.

6. Switch on the tunnel for few minutes to warm up.7. Now set the required velocity of airflow using DC motor controller knobs and

observe the displacement of the manometer liquid in all tubes, standing at

different levels and note them down.8. Note the manometer readings for different velocities to get required Cp.


12/26

Tabulation for Smooth Cylinder

S.No Port No.Cpx= (px- p) /

q1 1 0.573286

2 2-0.39413

3 3 -0.41205

4 4 -0.41205

5 5 -0.51954

6 6 0.340389

7 7 0.017915

8 8 -0.41205

9 9 0.143322

10 10 -0.37622

11 11 0.44788

12 12 0.985336

Along the cylinder surface

0.8

0.6

0.4

0.2

0

0.20.4

0.6

0.8

1

1.2

0 5 10 15

Cylinder

Cylinder


13/26


14/26

EXP NO: - 7 PRESSURE DISTRIBUTION OVER SYMMETRIC &

CAMBERED AEROFOIL AND ESTIMATION OF CLAND CD

Aim

To study the pressure distribution over a symmetric and cambered aerofoil and findout the lift and drag coefficient.

Apparatus:-

1) Low speed wind tunnel

2) Multi-tube Manometer3) Symmetric and cambered aerofoil model

Formulas used:-


Cp = (p- pi) / (p0- p) = (px pi) / q

Note: po= p+ (1/ 2) V2

po- p= (1/ 2) V2= q

Also

CN=(CPL CPU)dx/c

CL=C

NCos

CD= CNSin

Procedure:-

1. Prepare the low speed wind tunnel as per the instruction for the pressure

distribution.2. Ensure proper electrical installation and other safety.

3. Ensure proper and adequate power supply.

4. Fix the aerofoil in the test section over which the pressure distribution is to be

studied.

5. Connect the tubes bundle from multitube manometer to the correspondingtubes in the aerofoil model.

6. Switch on the tunnel for few minutes to warm up.7. Now set the required velocity of airflow using DC motor controller knobs and

observe the displacement of the manometer liquid in all tubes, standing atdifferent levels and note them down.

8. Note the manometer readings for different velocities to get required Cp.


15/26

Tab

lation for s

S.No

1

2

3

4

5

6

7

8

9

10

11

12

ymmetric

Port N

1

2

3

4

5

6

7

8

9

10

11

12

Cp

Along t

erofoil

o. Cp

lot for Sy

e chord le

x= (px- p

0.573286

-0.39413

-0.41205

-0.41205

-0.51954

0.340389

0.017915

-0.41205

0.143322

-0.37622

0.44788

0.985336

metric aer

gth

) / q

ofoil


16/26

Tab

S

Res

Thusthe g

lation for

.No

1

2

3

4

5

6

7

8

9

1011

12

lt:-

the pressuraph is plott

ambered a

ort No.

1

2

3

4

5

6

7

8

9

10

11

12

p Plot for

distributioed

rofoil

Cpx= (

0.57

-0.3

-0.4

-0.4

-0.5

0.34

0.01

-0.4

0.14

-0.3

0.4

0.98

he Cambe

Along t

over a Sy

x- p) /

3286

413

1205

1205

1954

0389

7915

1205

3322

622

788

5336

ed aerofoil

he chord le

metric an

ngth

Cambered aerofoil is calculated a d


17/26

EXP. NO: - 8 STUDY OF CALIBRATION OF SUPERSONIC WIND

TUNNEL

Aim

To estimate the efficiency of Supersonic wind tunnel

Apparatus Required

Supersonic wind tunnel

Manometer

Pitot tube

Formulas Used:-


Cpx= (2/ M2) [(px/p)-1]

(po/p) = [1 ((-1)/2)M2]

(/-1)

Procedure:-Study of calibration of supersonic wind tunnel is done in 3 methods

1. Determining by Mach number:-a) Run the tunnel

b) For a particular pressure take Manometer readings

c) Then calculate the Mach numbers at each port.b) See the Mach number in the test sections should be equal.

2. Measuring pitot pressures

1. Connect the Pitot tube in test section

2. Connect the wall static to the manometer3. Run the tunnel

4. Take the manometer reading

5. See that Mach number in the test section should be equal in all the places

3. Measuring static pressures

1. Take the cross section of the supersonic wind tunnel.2. Directly measure the length from throat to each port.

3. Take height at each port.4. Calculate the Mach number theoretically.

RESULT: Thus the calibration of supersonic wind tunnel is studied and its

efficiency is estimated


18/26

EXP. NO: - 9 VELOCITY DISTRIBUTION IN NOZZLE USING

SUPERSONIC FREE JET

Aim

1. To study the jet decay characteristics along the jet axis

2. To obtain lateral spread characteristics of the jet.

APPARATUS REQUIRED

Free-jet test setup, Traverse mechanism, Pitot probe for total pressure measurements, u-

tube Mercury manometer and meter scale, Barometer, Thermometer.

THEORY

Jets can be classified in a variety of ways. They can be classified as compressible

or incompressible jets based on the speed of the jet. They can also be classified as

laminar or turbulent jets based on the Reynolds number. Based on the jet cross section

shape, they are classified as circular or non-circular jets. Jets come under the category of

free shear flows. Jets which have free and unconstrained boundaries are called free jets.

Examples are nozzle exhaust jet into atmosphere, water jet issuing from a conduit or a tap

etc.

The flow of a jet can be divided into two regions; the mixing region and the

potential core. The potential core is that portion in the centre of the jet and near the exit

of the orifice through which the jet flows. In the potential core, the viscous effects are

negligible and the fluid can be considered to be inviscid. The first part of the mixing

region is the boundary of the jet near the exit of the nozzle. This mixing region widens as

the flow goes downstream. Far downstream, the whole jet will be a mixing region. In the

mixing region, the effects of viscosity and heat conduction have to be considered. In themixing region there are large variations in velocity and density.


19/26

DESCRIPTION OF EXPERIMENTAL SET-UP

The experimental set-up consists of a converging-diverging (CD) nozzle

connected to a high pressure compressor tank. The high pressure air is passed into the CD

nozzle through a moisture separator, dust collector and a pressure regulating valve to

control the mass flow rate through the duct. To laminarize the flow, three meshes are

fitted inside the diverging duct. The duct also consists of a settling chamber to which CD

nozzle is attached and the compressed air coming out as a free- jet into the open

atmosphere. The speed of the free-jet can be controlled by controlling the mass flow rate

through the pressure regulating valve.

CONDUCTING EXPERIMENT

In this experiment, the variation of jet total pressure along the centerline of a free

jet is measured to understand its decay characteristics. The jet is of circular shape. To

find its lateral spread characteristics the total pressure variations in the lateral direction ie.

Direction at different X positions i.e. X = 1, 2, 3, 4 are measured. The total pressure

probe is mounted in a traversing mechanism, which ensures the movement of the probe

along the jet axis.

CALCULATIONS

Velocity calculations:

Where,

P0is the total pressure

P is the static pressure

M is the Mach number

is the specific heat ratio ( fir air = 1.4)


20/26

DISTAN

CE

ALONG

X-AXIS

in(cm)

DISTAN

CE

ALONG

Y-AXIS

in(cm)

MANOM

ETER

READIN

G in

(cm)

Mach

No

Velocity

m/s

DISTAN

CE

ALONG

X-AXIS

in(cm)

DISTAN

CE

ALONG

Y-AXIS

in(cm)

MANOM

ETER

READIN

G in

(cm)

Mach

No

Velocity

m/s

0 13.5 0.49 170.86 0 5.9 0.33 114.82

3 13 0.48 167.84 3 5.4 0.32 109.97

6 11 0.45 155.05 6 5 0.30 105.92

9 7.2 0.36 126.48 9 4.3 0.28 98.38

12 2.8 0.23 79.66 12 3 0.24 82.42

14 2.4 0.21 73.82 14 2.6 0.22 76.80

0 10.5 0.44 151.65 0 5.4 0.32 109.97

3 9.9 0.42 147.44 3 5 0.30 105.92

6 7.9 0.38 132.28 6 4.5 0.29 100.60

9 5.5 0.32 110.96 9 3.5 0.26 88.92

12 4 0.27 94.95 12 2.7 0.22 78.24

14 3 0.24 82.42 14 2.4 0.21 73.82

0 12.9 0.48 167.23 0 5 0.30 105.92

3 12.2 0.47 162.87 3 4.8 0.30 103.82

6 7.2 0.36 126.48 6 3.9 0.27 93.78

9 5.4 0.32 109.97 9 3.5 0.26 88.92

12 3.9 0.27 93.78 12 2.5 0.22 75.32

14 2.9 0.23 81.05 14 2 0.19 67.45

0 8.2 0.39 134.68 0 4.3 0.28 98.38

3 7.4 0.37 128.17 3 4 0.27 94.95

6 6.2 0.34 117.63 6 3.7 0.26 91.38

9 5 0.30 105.92 9 3.4 0.25 87.66

12 2.8 0.23 79.66 12 3 0.24 82.42

14 2.7 0.22 78.24 14 2.2 0.20 70.71

0 7.4 0.37 128.17 0 4 0.27 94.95

3 6.8 0.35 123.02 3 3.7 0.26 91.38

6 5.5 0.32 110.96 6 3.4 0.25 87.66

9 4.5 0.29 100.60 9 2.8 0.23 79.66

12 3.4 0.25 87.66 12 2.2 0.20 70.71

14 2.6 0.22 76.80 14 1.8 0.18 64.02

0 6.5 0.35 120.36

3 6.2 0.34 117.63

6 5 0.30 105.92

9 4.1 0.28 96.11

12 3.2 0.24 85.08

14 2.4 0.21 73.82

6

7

8

9

10

0

1

2

3

4

5


21/26


22/26

From the above formula find out the Mach number.

M = u/a

a=

Where T is the Lab temperature

So u = Ma

TABULATION

Sl.NoDistance along

jet axis in cm

Difference

in heights

h in cm

Mach

Number Jet velocity in

m/s

1

2

3

4

5

PLOTS AND DISCUSSION

1. Variations of total pressure and local reference velocity with distance along centerline

of the jet

2. Variations of total pressure and local reference velocities in lateral direction at

different X values.

3. Comparisons of velocity profiles in lateral direction of the jet at different X values.

Result:

Thus the jet decay characteristics along the jet axis and lateral spread

characteristics of the jet are studied with graphs.


23/26

EXP. NO: - 9 FLOW VISUALIZATION USING SHADOWGRAPH

SYSTEM

Aim:-

To visualize the flow pattern in supersonic flow.

Apparatus Required

Supersonic free jet

Converging Diverging NozzleShadow graph System

Camera

Introduction

Flow visualization has played an important role in understanding the fundamentals of

fluids phenomena. One of the most important applications of flow visualization was dueto Osborne Reynolds, a prominent innovator in fluid dynamics, in 1883. He investigated

the circumstances of the transition from laminar to turbulent flow by injecting a liquid

dye into the water flowing through a long horizontal pipe. From these experiments camethe famous dimensionless Reynolds number for dynamic similarity. Another powerful

flow visualization tool is schlieren/shadowgraph technique, which is able to visualize

'invisible' density gradients and has been applied widely to study combustion,aerodynamics, fluid mechanics, etc.

Experimental Procedure

It consists of a light source which can be varied its intensity, lenses, screen and

cameras. Direct shadowgraph is shown in figure.


24/26

Shadowgraph image

Difference between Shadowgraph and Schlieren systems

Sl. No. Shadowgraph Schlieren

1 Displays a mere shadow Displays a focused image

2 Shows light ray displacement Shows ray refraction angle,

3 Illuminance level responds to Illuminance level responds to

4 No knife edge used Knife edge used forcutoff

Result:

Thus the study of shadow graph system is studied and the shadow graph image is

taken.

2

2

x

n

xn


25/26

EXP NO: - 11 PRESSURE DISTRIBUTION OVER WEDGE

AEROFOIL AND ESTIMATION OF CLAND CD

Aim:-

To study the pressure distribution over a Wedge aerofoil.

Apparatus:-

1) Low speed wind tunnel2) Multi-tube Manometer

3) Wedge aerofoil model

Formulas used:-


Cp = (p- pi) / (p0- p) = (px pi) / q

Note: po= p+ (1/ 2) V2

po- p= (1/ 2) V2= q

Also

CN=(CPL CPU)dx/c

CL=CNCos

CD= CNSin

Procedure:-1. Prepare the low speed wind tunnel as per the instruction for the pressure

distribution on the Wedge aerofoil.

2. Ensure proper electrical installation and other safety.3. Ensure proper and adequate power supply.

4. Fix the aerofoil in the test section over which the pressure distribution is to be

studied.5. Connect the tubes bundle from multitube manometer to the corresponding

tubes in the aerofoil model.

6. Switch on the tunnel for few minutes to warm up.7. Now set the required velocity of airflow using DC motor controller knobs andobserve the displacement of the manometer liquid in all tubes, standing at

different levels and note them down.

8. Note the manometer readings for different velocities to get required Cp.


26/26

Tab

Res

Thus

lation :-

.No

1

2

3

4

5

6

7

8

9

10

11

12

A

lt:-

the pressur

Port No.

1

2

3

4

5

6

7

8

9

10

11

12

We

ong the ch

distributio

Cpx

0

-

-

-

-

0

0

-

0

-

0

ge aeroflil

rd length

over Wed

(px- p)

q

.573286

.39413

.41205

.41205

.51954

.340389

.017915

.41205

.143322

.37622

.44788

.985336

e aerofoil i

/

calculated and the gra h is plotted.

09 AE2258 Aerodynamics Lab Manual

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