- •Textbook Series
- •Contents
- •1 Overview and Definitions
- •Overview
- •General Definitions
- •Glossary
- •List of Symbols
- •Greek Symbols
- •Others
- •Self-assessment Questions
- •Answers
- •2 The Atmosphere
- •Introduction
- •The Physical Properties of Air
- •Static Pressure
- •Temperature
- •Air Density
- •International Standard Atmosphere (ISA)
- •Dynamic Pressure
- •Key Facts
- •Measuring Dynamic Pressure
- •Relationships between Airspeeds
- •Airspeed
- •Errors and Corrections
- •V Speeds
- •Summary
- •Questions
- •Answers
- •3 Basic Aerodynamic Theory
- •The Principle of Continuity
- •Bernoulli’s Theorem
- •Streamlines and the Streamtube
- •Summary
- •Questions
- •Answers
- •4 Subsonic Airflow
- •Aerofoil Terminology
- •Basics about Airflow
- •Two Dimensional Airflow
- •Summary
- •Questions
- •Answers
- •5 Lift
- •Aerodynamic Force Coefficient
- •The Basic Lift Equation
- •Review:
- •The Lift Curve
- •Interpretation of the Lift Curve
- •Density Altitude
- •Aerofoil Section Lift Characteristics
- •Introduction to Drag Characteristics
- •Lift/Drag Ratio
- •Effect of Aircraft Weight on Minimum Flight Speed
- •Condition of the Surface
- •Flight at High Lift Conditions
- •Three Dimensional Airflow
- •Wing Terminology
- •Wing Tip Vortices
- •Wake Turbulence: (Ref: AIC P 072/2010)
- •Ground Effect
- •Conclusion
- •Summary
- •Answers from page 77
- •Answers from page 78
- •Questions
- •Answers
- •6 Drag
- •Introduction
- •Parasite Drag
- •Induced Drag
- •Methods of Reducing Induced Drag
- •Effect of Lift on Parasite Drag
- •Aeroplane Total Drag
- •The Effect of Aircraft Gross Weight on Total Drag
- •The Effect of Altitude on Total Drag
- •The Effect of Configuration on Total Drag
- •Speed Stability
- •Power Required (Introduction)
- •Summary
- •Questions
- •Annex C
- •Answers
- •7 Stalling
- •Introduction
- •Cause of the Stall
- •The Lift Curve
- •Stall Recovery
- •Aircraft Behaviour Close to the Stall
- •Use of Flight Controls Close to the Stall
- •Stall Recognition
- •Stall Speed
- •Stall Warning
- •Artificial Stall Warning Devices
- •Basic Stall Requirements (EASA and FAR)
- •Wing Design Characteristics
- •The Effect of Aerofoil Section
- •The Effect of Wing Planform
- •Key Facts 1
- •Super Stall (Deep Stall)
- •Factors that Affect Stall Speed
- •1g Stall Speed
- •Effect of Weight Change on Stall Speed
- •Composition and Resolution of Forces
- •Using Trigonometry to Resolve Forces
- •Lift Increase in a Level Turn
- •Effect of Load Factor on Stall Speed
- •Effect of High Lift Devices on Stall Speed
- •Effect of CG Position on Stall Speed
- •Effect of Landing Gear on the Stall Speed
- •Effect of Engine Power on Stall Speed
- •Effect of Mach Number (Compressibility) on Stall Speed
- •Effect of Wing Contamination on Stall Speed
- •Warning to the Pilot of Icing-induced Stalls
- •Stabilizer Stall Due to Ice
- •Effect of Heavy Rain on Stall Speed
- •Stall and Recovery Characteristics of Canards
- •Spinning
- •Primary Causes of a Spin
- •Phases of a Spin
- •The Effect of Mass and Balance on Spins
- •Spin Recovery
- •Special Phenomena of Stall
- •High Speed Buffet (Shock Stall)
- •Answers to Questions on Page 173
- •Key Facts 2
- •Questions
- •Key Facts 1 (Completed)
- •Key Facts 2 (Completed)
- •Answers
- •8 High Lift Devices
- •Purpose of High Lift Devices
- •Take-off and Landing Speeds
- •Augmentation
- •Flaps
- •Trailing Edge Flaps
- •Plain Flap
- •Split Flap
- •Slotted and Multiple Slotted Flaps
- •The Fowler Flap
- •Comparison of Trailing Edge Flaps
- •and Stalling Angle
- •Drag
- •Lift / Drag Ratio
- •Pitching Moment
- •Centre of Pressure Movement
- •Change of Downwash
- •Overall Pitch Change
- •Aircraft Attitude with Flaps Lowered
- •Leading Edge High Lift Devices
- •Leading Edge Flaps
- •Effect of Leading Edge Flaps on Lift
- •Leading Edge Slots
- •Leading Edge Slat
- •Automatic Slots
- •Disadvantages of the Slot
- •Drag and Pitching Moment of Leading Edge Devices
- •Trailing Edge Plus Leading Edge Devices
- •Sequence of Operation
- •Asymmetry of High Lift Devices
- •Flap Load Relief System
- •Choice of Flap Setting for Take-off, Climb and Landing
- •Management of High Lift Devices
- •Flap Extension Prior to Landing
- •Questions
- •Annexes
- •Answers
- •9 Airframe Contamination
- •Introduction
- •Types of Contamination
- •Effect of Frost and Ice on the Aircraft
- •Effect on Instruments
- •Effect on Controls
- •Water Contamination
- •Airframe Aging
- •Questions
- •Answers
- •10 Stability and Control
- •Introduction
- •Static Stability
- •Aeroplane Reference Axes
- •Static Longitudinal Stability
- •Neutral Point
- •Static Margin
- •Trim and Controllability
- •Key Facts 1
- •Graphic Presentation of Static Longitudinal Stability
- •Contribution of the Component Surfaces
- •Power-off Stability
- •Effect of CG Position
- •Power Effects
- •High Lift Devices
- •Control Force Stability
- •Manoeuvre Stability
- •Stick Force Per ‘g’
- •Tailoring Control Forces
- •Longitudinal Control
- •Manoeuvring Control Requirement
- •Take-off Control Requirement
- •Landing Control Requirement
- •Dynamic Stability
- •Longitudinal Dynamic Stability
- •Long Period Oscillation (Phugoid)
- •Short Period Oscillation
- •Directional Stability and Control
- •Sideslip Angle
- •Static Directional Stability
- •Contribution of the Aeroplane Components.
- •Lateral Stability and Control
- •Static Lateral Stability
- •Contribution of the Aeroplane Components
- •Lateral Dynamic Effects
- •Spiral Divergence
- •Dutch Roll
- •Pilot Induced Oscillation (PIO)
- •High Mach Numbers
- •Mach Trim
- •Key Facts 2
- •Summary
- •Questions
- •Key Facts 1 (Completed)
- •Key Facts 2 (Completed)
- •Answers
- •11 Controls
- •Introduction
- •Hinge Moments
- •Control Balancing
- •Mass Balance
- •Longitudinal Control
- •Lateral Control
- •Speed Brakes
- •Directional Control
- •Secondary Effects of Controls
- •Trimming
- •Questions
- •Answers
- •12 Flight Mechanics
- •Introduction
- •Straight Horizontal Steady Flight
- •Tailplane and Elevator
- •Balance of Forces
- •Straight Steady Climb
- •Climb Angle
- •Effect of Weight, Altitude and Temperature.
- •Power-on Descent
- •Emergency Descent
- •Glide
- •Rate of Descent in the Glide
- •Turning
- •Flight with Asymmetric Thrust
- •Summary of Minimum Control Speeds
- •Questions
- •Answers
- •13 High Speed Flight
- •Introduction
- •Speed of Sound
- •Mach Number
- •Effect on Mach Number of Climbing at a Constant IAS
- •Variation of TAS with Altitude at a Constant Mach Number
- •Influence of Temperature on Mach Number at a Constant Flight Level and IAS
- •Subdivisions of Aerodynamic Flow
- •Propagation of Pressure Waves
- •Normal Shock Waves
- •Critical Mach Number
- •Pressure Distribution at Transonic Mach Numbers
- •Properties of a Normal Shock Wave
- •Oblique Shock Waves
- •Effects of Shock Wave Formation
- •Buffet
- •Factors Which Affect the Buffet Boundaries
- •The Buffet Margin
- •Use of the Buffet Onset Chart
- •Delaying or Reducing the Effects of Compressibility
- •Aerodynamic Heating
- •Mach Angle
- •Mach Cone
- •Area (Zone) of Influence
- •Bow Wave
- •Expansion Waves
- •Sonic Bang
- •Methods of Improving Control at Transonic Speeds
- •Questions
- •Answers
- •14 Limitations
- •Operating Limit Speeds
- •Loads and Safety Factors
- •Loads on the Structure
- •Load Factor
- •Boundary
- •Design Manoeuvring Speed, V
- •Effect of Altitude on V
- •Effect of Aircraft Weight on V
- •Design Cruising Speed V
- •Design Dive Speed V
- •Negative Load Factors
- •The Negative Stall
- •Manoeuvre Boundaries
- •Operational Speed Limits
- •Gust Loads
- •Effect of a Vertical Gust on the Load Factor
- •Effect of the Gust on Stalling
- •Operational Rough-air Speed (V
- •Landing Gear Speed Limitations
- •Flap Speed Limit
- •Aeroelasticity (Aeroelastic Coupling)
- •Flutter
- •Control Surface Flutter
- •Aileron Reversal
- •Questions
- •Answers
- •15 Windshear
- •Introduction (Ref: AIC 84/2008)
- •Microburst
- •Windshear Encounter during Approach
- •Effects of Windshear
- •“Typical” Recovery from Windshear
- •Windshear Reporting
- •Visual Clues
- •Conclusions
- •Questions
- •Answers
- •16 Propellers
- •Introduction
- •Definitions
- •Aerodynamic Forces on the Propeller
- •Thrust
- •Centrifugal Twisting Moment (CTM)
- •Propeller Efficiency
- •Variable Pitch Propellers
- •Power Absorption
- •Moments and Forces Generated by a Propeller
- •Effect of Atmospheric Conditions
- •Questions
- •Answers
- •17 Revision Questions
- •Questions
- •Answers
- •Explanations to Specimen Questions
- •Specimen Examination Paper
- •Answers to Specimen Exam Paper
- •Explanations to Specimen Exam Paper
- •18 Index
Propellers 16
Asymmetric Blade Effect
In general, the propeller shaft will be inclined upwards from the direction of flight due to the angle of attack of the aircraft. This gives the down-going propeller blade a greater effective angle of attack than the up-going blade. The down-going (right) blade will generate more thrust. The difference in thrust on the two sides of the propeller disc will give a yawing moment to the left with a clockwise rotating propeller in a nose-up attitude.
Asymmetric blade effect will be greatest at full power and low airspeed (high angle of attack).
Effect of Atmospheric Conditions
Changes of atmospheric pressure or temperature will cause a change of air density. This will affect:
•the power produced by the engine at a given throttle position.
•the resistance to rotation of the propeller (its drag).
An increase in air density will increase both the engine power and the propeller drag. The change in engine power is more significant than the change in propeller drag.
Engine and Propeller Combined
If the combined effect of an engine and propeller is being considered, it is the engine power change which will determine the result. For an engine driving a fixed pitch propeller:
•if density increases, RPM will increase.
•if density decreases, RPM will decrease.
Engine Alone
If the shaft power required to drive the propeller is being considered, then it is only the propeller torque which needs to be taken into account. To maintain the RPM of a fixed pitch propeller:
•if density increases, power required will increase.
•if density decreases, power required will decrease.
Propellers 16
517
16 Questions
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1. |
As a result of gyroscopic precession, it can be said that: |
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a. |
any pitching around the longitudinal axis results in a yawing moment. |
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b. |
any yawing around the normal axis results in a pitching moment. |
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c. |
any pitching around the lateral axis results in a rolling moment. |
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d. |
any rolling around the longitudinal axis results in a pitching moment. |
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2. |
A propeller rotating clockwise as seen from the rear, creates a spiralling slipstream |
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that tends to rotate the aeroplane to the: |
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a. |
right around the normal axis, and to the left around the longitudinal axis. |
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b. |
right around the normal axis, and to the right around the longitudinal axis. |
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c. |
left around the normal axis, and to the left around the longitudinal axis. |
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d. |
left around the normal axis, and to the right around the longitudinal axis. |
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3. |
The reason for variations in geometric pitch (twisting) along a propeller blade is |
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that it: |
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a. |
prevents the portion of the blade near the hub from stalling during cruising |
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flight. |
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b. |
permits a relatively constant angle of attack along its length when in cruising |
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flight. |
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c. |
permits a relatively constant angle of incidence along its length when in |
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cruising flight. |
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d. |
minimizes the gyroscopic effect. |
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4. |
The geometric pitch of a propeller is: |
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a. |
the distance it would move forward in one revolution if there were no slip. |
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b. |
the angle the propeller shaft makes to the plane of rotation. |
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c. |
the distance the propeller actually moves forward in one revolution. |
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d. |
the angle the propeller chord makes to the relative airflow. |
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5. |
Propeller ‘slip’ is: |
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a. |
the airstream in the wake of the propeller. |
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b. |
the amount by which the distance covered in one revolution falls short of the |
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geometric pitch. |
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c. |
the increase in RPM which occurs during take-off. |
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d. |
the change of blade angle from root to tip. |
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6. |
The distance a propeller actually advances in one revolution is: |
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a. |
twisting. |
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b. |
effective pitch. |
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c. |
geometric pitch. |
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d. |
blade pitch. |
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7. |
Blade angle of a propeller is defined as the angle between the: |
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a. |
angle of attack and chord line. |
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b. |
angle of attack and line of thrust. |
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c. |
chord line and plane of rotation. |
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d. |
thrust line and propeller torque. |
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8. |
Propeller efficiency is the: |
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a. |
actual distance a propeller advances in one revolution. |
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b. |
ratio of thrust horsepower to shaft horsepower. |
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c. |
ratio of geometric pitch to effective pitch. |
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d. |
ratio of TAS to RPM. |
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9. |
A fixed pitch propeller is designed for best efficiency only at a given combination |
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of: |
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a. |
airspeed and RPM. |
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b. |
airspeed and altitude. |
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c. |
altitude and RPM. |
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d. |
torque and blade angle. |
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10. |
Which statement is true regarding propeller efficiency? Propeller efficiency is the: |
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difference between the geometric pitch of the propeller and its effective pitch. |
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b. |
actual distance a propeller advances in one revolution. |
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c. |
ratio of thrust horsepower to shaft horsepower. |
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d. |
ratio between the RPM and number of blade elements. |
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11. |
Which statement best describes the operating principle of a constant speed |
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propeller? |
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a. |
As throttle setting is changed by the pilot, the prop governor causes pitch |
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angle of the propeller blades to remain unchanged. |
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b. |
The propeller control regulates the engine RPM and in turn the propeller RPM. |
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c. |
A high blade angle, or increased pitch, reduces the propeller drag and allows |
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more engine power for takeoffs. |
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d. |
As the propeller control setting is changed by the pilot, the RPM of the |
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engines remains constant as the pitch angle of the propeller changes. |
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12. |
When does asymmetric blade effect cause the aeroplane to yaw to the left? |
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a. |
When at high angles of attack. |
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b. |
When at high airspeeds. |
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c. |
When at low angles of attack. |
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d. |
In the cruise at low altitude. |
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13. |
The left turning tendency of an aeroplane caused by asymmetric blade effect is the |
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result of the: |
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a. |
gyroscopic forces applied to the rotating propeller blades acting 90° in |
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advance of the point the force was applied. |
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b. |
clockwise rotation of the engine and the propeller turning the aeroplane |
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counter-clockwise. |
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c. |
propeller blade descending on the right, producing more thrust than the |
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ascending blade on the left. |
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d. |
the rotation of the slipstream striking the tail on the left. |
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519
16 Questions
14. |
With regard to gyroscopic precession, when a force is applied at a point on the rim |
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of a spinning disc, the resultant force acts in which direction and at what point? |
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a. |
In the same direction as the applied force, 90° ahead in the plane of rotation. |
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b. |
In the opposite direction of the applied force, 90° ahead in the plane of |
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rotation. |
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c. |
In the opposite direction of the applied force, at the point of the applied |
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force. |
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d. |
In the same direction as the applied force, 90° ahead of the plane of rotation |
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when the propeller rotates clockwise, 90° retarded when the propeller rotates |
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counter-clockwise. |
15. |
The angle of attack of a fixed pitch propeller: |
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a. |
depends on forward speed only. |
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b. |
depends on forward speed and engine rotational speed. |
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c. |
depends on engine rotational speed only. |
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d. |
is constant for a fixed pitch propeller. |
16. |
Counter-rotating propellers are: |
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a. |
propellers which rotate counter clockwise. |
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b. |
propellers which are geared to rotate in the opposite direction to the engine. |
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c. |
two propellers driven by separate engines, rotating in opposite directions. |
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d. |
two propellers driven by the same engine, rotating in opposite directions. |
17. |
If engine RPM is to remain constant on an engine fitted with a variable pitch |
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propeller, an increase in engine power requires: |
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16 |
a. |
a decrease in blade angle. |
Questions |
b. |
a constant angle of attack to be maintained to stop the engine from |
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overspeeding. |
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c. |
an increase in blade angle. |
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d. |
the prop control lever to be advanced. |
520
Questions 16
Questions 16
521