Cessna 310 Propeller Theory
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
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