Cessna 310 Propeller Theory

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  • Topic: Propeller, Rotation, Jet engine
  • Pages : 7 (1475 words )
  • Download(s) : 737
  • Published : March 18, 2013
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Table of Contents

Page 1 - Contents

Page 2 - Introduction

Page 2 - Activity 1: Cessna-310 Performance Data

Page 3-4 - Activity 2: Propeller Parameter Definitions

Page 4 - Activity 3: Results of Engine RPM vs Fuel Flow

Page 5-6- Activity 4: Axial Momentum Theory

Page 7-8 - Activity 5: Propeller Efficiency & Power Coefficient

Page 8-9- Activity 6: Fuel Flow

Page 9 - Activity 7: Conclusion

Page 10- Reference

Introduction

The function of a propeller on an aircraft is to provide propulsive force. This lab report was aimed at studying and analysing the propeller and some engine properties of a Cessna 310R. The axial momentum theory, advance ratio and the energy method for fuel flow estimation are used in this analysis.

CESSNA 310 PERFORMANCE DATA

ACTIVITY 1

MTOW: 5, 500 pounds (2576 kg)
Fuel weight: 102.00 gal or (618 L)
Wing span: 35 ft 0 in (10.67 m)
Engine type: Two 213kW (285hp) Continental IO-520-MB fuel injected piston engines. Propeller diameter: 74-76 in
No. of blades/prop: 3
Wing area: 16.3m2 (175sq ft).
Engine max continuous power: 39 in.hg. and 2500 RPM
Take-off power: 285 hp (213 kW)
Fuel flow: 120 lts/hr
Take-off speed: 92 kts or 47.328m/s
Cruise speed: 267km/h (144kts)
Cruise altitude: 19,750ft.
Range: 1170km (632nm) - 1617km (873nm)

Definition of propeller parameters

ACTIVITY 2

Forward speed: The rate of movement/ advancement of the propeller relative to the air. Rpm: This is the rotational speed of the propeller, it is measured in revolutions per min. Mtip : Mach Number tip, this is the quality of the propeller tip to reach the mach number as a result of increase in RPM. No. of blade: A propeller has a number of blades, in a Cessna 310, the number of blades is 3. Diameter (d): the distance across the circle swept by the extreme tips of the propeller blades. In the majority of cases, the larger the diameter the greater the propeller efficiency. Pitch ((): The pitch is a measure of the orientation of the propeller on a plane normal to the axis of rotation. reference line for the calculation of the pitch is the chord. Type of blade section: cross section of a propeller blade in a plane parallel to that containing the axis of rotation. Chord distribution along radius: This is the various distribution of the length of the chord from the leading edge to the trailing edge as a result of geometrical shape of the blasé section. Chord length at the hub is greater than at the tip. Tip geometry: This is the extreme part of a propeller at the tip which is geometrically thinner than the rest of the propeller blade. Hub geometry: This is the root of the propeller which is quiet bigger than the rest of the propeller blade.

Propeller stream tube: This is the axial direction and change in flow momentum along a stream-tube starting upstream, passing through the propeller, and through the downstream. [pic]

Propeller disk: This is total area on which the propeller rotates.. Propeller is considered as a rotating disk instead of consisting the blades which are rotating in the air. The rotating disk imparts axial momentum to the air passing through it.

ACTIVITY 3

Measuring engine rpm vs fuel flow from cockpit instrumentation. The table below shows the measured values of the fuel flow at 1000 rpm, 1500 rpm and 2000 rpm.

|RPM |FUEL FLOW (kg/s) | |1100 |0.003527916kg/s | |1500 |0.004787886kg/s | |2000 |0.007811814kg/s |

ACTIVITY 4

Axial Momentum Theory

This is a theoretical mechanism in which the rotating power of a propeller is converted into useful thrust. In this theory, the propeller is considered as a rotating disk instead of consisting the blades which are rotating in the air....
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