Thermofluid Mechanics and Mechanical Design lab report

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FACULTY OF ENGINEERING AND TECHNOLOGY

UK DEGREE TRANSFER PROGRAMME IN MECHANICAL ENGINEERING

EGM 371

Thermofluid Mechanics and Mechanical Design 2

Laboratory Reports


Contents

Experiment 1        

Experiment 2        7


Experiment 1

Free forced vortex flow

Objectives

Free and Forced Vortex Flow

To determine the surface profile and to study energy distribution of Vortex

Theory

When liquid in a vessel is rotated about a vertical axis for a certain period, the liquid will be depressed down at the axis of rotation and risen up near the wall of the vessel. This type of flow in which a liquid flows continuously round a curved path about an axis of rotation is called vortex flow. Forced vortex flow is the vortex flow formed due to some external force, example torque while free vortex flow is the vortex flow without the helping of external force. 

Procedure

  1. Fill up around ½ of the clear water into Acrylic tank
  2. To avoid any air bubble through the water tube connecting between manometer leg and pitot tube.
  3. Rotate the cylinder and increase the angular speed in a certain value (89rpm), than mark down the value using stop watch and the length on outside cylinder.
  4. Pitot tip must be carefully adjusted to close to free surface while starting at centre of vortex.
  5. Shift pitot tip to right hand side around 2cm and mark the reading of Z & H values.
  6. Allow water movement inner cylinder to slow down to nearly zero angular velocity, then open drain value under cylinder, fully free vortex will be induced with some noise.


Results and Analysis

Calculation:

In calculation part, we are using the equation, Z= (ω2r2)/ 2g

ω = 89rpm

= (89x2π)/60

= 9.32 rad/sec           

When r = 2cm = 0.02m

Z= (9.322 x 0.022) / (2x9.81)

   = 1.77 x 10-3 m

   = 0.177 cm

When r = 4cm = 0.04m

Z= (9.322 x 0.042) / (2x9.81)

   = 7.084 x 10-3 m

   = 0.7084 cm

When r = 6cm = 0.06m

Z= (9.322 x 0.062) / (2x9.81)

   = 0.01594 m

   = 1.594 cm

When r = 8cm = 0.08m

Z= (9.322 x 0.082) / (2x9.81)

   = 0.02833 m

   = 2.833 cm

When r = 10cm = 0.10m

Z= (9.322 x 0.102) / (2x9.81)

   = 0.04427 m

   = 4.427 cm

Discussion and Conclusion

Observation of the vortex phenomena:

  1. Measure water in water manometer balance.
  2. Water doesn’t flow in tube when it’s adjusted.
  3. The reading was taken at the free surface of water that reading was hard to get using a ruler.
  4. Length of tube was not changed
  5. The water moves in a twisted style while it was realeased.
  6. The diameter at free vortex decrease as water released.
  7. As the vortex get small and velocity increase same surf of sound  occurs.
  8. Sounds get louder when the water increasing.

In this experiment, we were dealing with water (liquid). Liquid is very difficult to be measured as it always moving randomly. While doing the experiment, we have a great difficulty in measuring the Z value, as the curve of vortex flow is not stable.

Besides, the manometer seem like not function very well. The reading was not changing throughout the experiment. Therefore, we were having problem in the H values as well.

As a conclusion, we were failed to meet the actual set of result required in this experiment. Even though the experiment was failed, we did learn the theory of vortex flow. This experiment had helped us understanding the concept very much.


Experiment 2

Wind Tunnel

Objectives

Wind Tunnel

To investigate the effect of the attach angles of the aerofoil in the wind tunnel on the lift and drag coefficient of the body.

Theory

This is important equipment that is very widely used in fluid mechanics to perform various tests on the model before fabricating the actual prototype. The tests that can be conducted in the model are including drag and lift coefficients which are important for automobile design. Drag sometimes is called as air resistance or fluid resistance. Drag forces act in a direction parallel to the relative approach flow velocity. The equation for the drag coefficient may be in tem of: Drag= ½ CDAρU2.  Lift forces is defined perpendicular to the relative approach flow direction. The equation for the lift coefficient may be in term of: LIFT= ½ CLAU2.

Procedure

  1. First, start the measurement by the angle of attack  is 0 degree which is set on the NACA 0015 airfoil.
  2. Counter weight and x, y distance is adjusted at two component balance so that Fx and Fy can be read from load cells directly.
  3. The blow is started up by the air speed 20 m/sec.
  4. From the lab manual, we knew that the Fx and Fy is read as drag and lift. Then the reading of the 1st reading of Fx and Fy is recorded.
  5. After that, the angle of attack is adjusted to 2, 4, 5, and 6 degree respectively and also repeats the step 2. The reading of Fx and Fy is recorded at every measurement as well.
  6. After finish the observation of speed 20 m/sec, repeat the step 1 to 5 for speed 12 m/sec.
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Results and Analysis

Speed 20 m/sec

Speed 12 m/sec

Calculations and formula used

Chord length = 0.22m, Wing length = 0.04m, ρ = 1.2kg/m3

A = Chord length x Wing length

= 0.22m x 0.04m

= 0.0088m2

Cd = Drag/AρU2

CL = Lift/AρU2

For example, speed 12 m/sec (RUN 2)

Cd = Drag/AρU2

     = 0.250/ [0.0088x1.2x (0.8)2]

     = 36.99

CL = Lift/AρU2

     = 0.668/ [0.0088x1.2x (0.8)2]

     = 98.84

Graph:

Speed 20 m/sec

Angle of attack, vs. CD

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