Aerodynamics of a Rocket

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Aerodynamics of a Rocket

• Mentor A/P Andrew Wee

• Group Members
• Darwin Gosal
• Martin Lee
• Tan Hai Siong
• Tan Kim Seng

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Outline

• Introduction
• Theoretical Background
• Procedure / Set Up
• Results and Analysis
• Conclusion
• Improvements
• Further Experiment

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Introduction

• These fin shapes with angle ? varying from 45º to
  90º (in increasing steps of 5º) will be inserted
  onto the rocket body shaft during the experiment.
  A wind tunnel will be used to channel moving air
  currents upward towards the rocket body. An
  empirical relation between the resulting drag
  force and the angle ? would be obtained from the
  experimental results. The interdependence between
  the wind speed with these two variables was
  investigated.

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Introduction
5
Theoretical Background

• Viscous Drag - drag due to skin friction
• Form Drag - drag due to the separation of the
  flow from the body which results in the
  alteration of pressure distribution.

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Theoretical Background

• The expressions for the coefficient of viscosity
  ? and the shearing stress ? in terms of the
  properties of the fluid of the flow are
• ? 1/3 ? c L
• ? ? ?u / ?y

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Theoretical Background

• The concept of a shearing stress isRate of
  transfer of downstream momentum in a direction
  lateral to the flow.
• The shearing stress at the surface
  ? ? ?u / ?y is the skin friction (Force per
  unit area.)
• This is exerted by the fluid on the surface in
  the tangential direction.

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Theoretical Background
1. Eulers Equation may be written as
2. After summing up the pressure and shear forces
on an element in a boundary layer -
3. We thus obtain the boundary layer equation of
motion
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Theoretical Background
4. The continuity equation for incompressible
flow -
5. The boundary layer equation of motion and the
continuity equation are the equations available
for the solution of our aerodynamic problem.
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Theoretical Background

• For the steady flow of the incompressible viscous
  fluid along a flat plate

2. Upon solving these differential equations, we
obtained an expression for the drag force drag
per unit area
Figure 3.3 - Boundary Layer on a flat plate
where ue is the speed of wind of the wind tunnel
as measured by the anemometer.
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Procedure / Set Up
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Results Analysis
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Results Analysis
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Results Analysis
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Results Analysis
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Results Analysis
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Results Analysis
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Results Analysis
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Results Analysis
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Conclusion .

• There is a clear, direct relationship between
  resistive force and the variables and furthermore
  more that it is an increasing function of both of
  them.
• It has also been observed that with higher wind
  speed, the resistive force increases more quickly
  with increasing angles.

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Problems Improvements
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Problems Improvements
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Problems Improvements
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Problems Improvements
q
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Problems Improvements
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Further Experiment
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Further Experiment
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Further Experiment
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Further Experiment
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THE END
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Weight Balance
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Pulley
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Anemometer
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Rocket Body
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Force Transducer
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Wind Tunnel
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Pivot
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