1. A propeller blade is twisted along its length in order to:
a. give a progressively increasing blade angle from root to tip
b. give a progressively increasing angle of attack from root to tip when the propeller is rotating
c. compensate for the decreasing linear speed of the blade from root to tip
d. maintain the most efficient angle of attack along the whole length of the propeller blade when the propeller is rotating
2. Blade angle _________ from the hub to the tip of a propeller blade in order to maintain an optimal ____________ from hub to tip during propeller rotation. a. increases angle of attack
b. decreases geometric pitch c. increases effective pitch d. decreases angle of attack
3. As an aircraft with a variable-pitch, constant-speed propeller accelerates along the runway:
a. the angle of attack will decrease and the engine RPM remain constant
b. the blade pitch angle increases, maintaining a constant angle of attack and constant RPM
c. the angle of attack will remain constant and the engine RPM will increase
d. the linear velocity of the propeller tip will gradually decrease
4. In a dive, with the throttle setting constant, the engine RPM of an aircraft fitted with a fixed-pitch propeller will:
a. decrease as the airspeed increases b. remain constant whatever the airspeed c. increase if the airspeed is allowed to increase
d. decrease as long as the throttle setting is not changed
5. In a single-engine, propeller-driven aircraft, the torque reaction of a clockwise rotating propeller (as seen from the pilot’s seat) will tend to cause:
a. left roll and right yaw during take off b. left roll and left yaw during take off c. right roll and right yaw during take off d. left yaw and right roll during take off
6. Which of the following combinations will decrease the angle of attack of a fixed pitch propeller blade?
a. Increased TAS and increased RPM b. Increased TAS and decreased RPM c. Decreased TAS and increased RPM d. Decreased TAS and decreased RPM
7. Which of the following combinations will increase the angle of attack of a fixed pitch propeller blade?
a. Increased TAS and increased RPM b. Increased TAS and decreased RPM c. Decreased TAS and increased RPM d. Decreased TAS and decreased RPM
8. The advantage of a constant speed propeller over a fixed pitch propeller is that:
a. a greater maximum thrust is available b. a higher maximum efficiency is attained c. more blade surface area is made available
d. optimal efficiency is achieved over a wide speed range
9. The angle of attack of a fixed, coarse-pitch propeller on a touring light aircraft:
a. will be lower during the take-off run than in flight b. will be optimal in all flight conditions
c. will be most efficient at the cruising speeds published in the pilot’s operating manual
d. will decrease with decreasing airspeed at constant engine RPM 10. A propeller blade is twisted from root to tip:
a. to provide maximum thrust at the root b. to provide maximum thrust at the tip
c. so that propeller efficiency remains high, at any engine RPM d. so that thrust remains approximately constant along the whole length
of the propeller blade, at any engine RPM
11. The angle of attack of a fixed-pitch propeller designed for cruising flight is: a. optimal for steady cruising flight only
b. increases with an increase in TAS c. decreases with an increase in RPM d. will always be positive in a power off glide
12. Propeller-blade angle of attack is the angle between the blade chord-line and the:
a. plane of rotation of the propeller b. aeroplane’s gradient of climb c. the airflow relative to the propeller d. helix angle
13. What is the purpose of increasing the number of propeller blades? a. To reduce noise
b. To improve power absorption
c. To increase the efficiency of the variable pitch mechanism d. To enable a longer undercarriage to be fitted
14. What would be the gyroscopic effect of a clockwise rotating propeller (viewed from the pilot’s seat) on a single-engine, tail-wheel aircraft as it raises its tail during the take off run?
a. The aircraft would yaw to the right b. The aircraft would yaw to the left c. The aircraft would roll to the right d. The aircraft would roll to the left
15. During the take-off roll, what effect does torque have on an aircraft with an anti-clockwise rotating propeller, as seen from the pilot’s seat?
a. Weight on left wheel decreased, weight on right wheel increased b. Weight on left wheel increased, weight on right wheel remains
constant
c. Weight on left wheel increased, weight on right wheel decreased d. Weight on right wheel increased, weight on left wheel remains
constant
16. Which of the following definitions of propeller parameters is correct? a. Blade Angle is the angle between chord line and the relative airflow b. Critical tip speed is the propeller speed at which there is a risk of the
flow separating at some part of the propeller
c. Blade angle of attack is the angle between the blade chord line and propeller’s plane of rotation
d. Geometric pitch is the theoretical distance that the propeller travels forward in one rotation
17. Which of the following gives the most correct explanation of why a propeller’s blade angle decreases from root to tip?
a. To compensate for the change in blade cross section from root to tip
b. To provide increased thrust at the root c. To provide increased thrust at the tip
d. To compensate for the increase in rotational velocity from root to tip.
18. On take off, why is it that a tail-wheel aircraft displays a greater tendency to swing than a nose-wheel aircraft?
a. Because the propeller of a tail-wheel aircraft always rotates anticlockwise
b. Because torque effect in a tail-wheel aircraft counters slipstream effect
c. Because the tail-wheel aircraft is subject to asymmetric blade effect and gyroscopic effect, in addition to slipstream and torque effect d. Because the nose-wheel aircraft is not subject to torque effect and
slipstream effect
19. When power is applied, why do aircraft in straight and level flight show a tendency to yaw?
a. Because of the gyroscopic effect of the propeller
b. Because of the slipstream effect and torque effect of the propeller c. Because most aircraft are fitted with an off-set fin
d. Because the pilot always applies rudder when increasing power 20. On an aircraft fitted with a fixed pitch propeller, why does a change in airspeed
always cause a corresponding change in engine RPM, even though the pilot may not move the throttle lever?
a. Because a change in airspeed causes a change in inlet manifold pressure which affects engine power output
b. Because an increase in airspeed causes a decrease in propeller angle of attack , thus reducing propeller torque, while a decrease in airspeed has the opposite effect
c. Because of the asymmetric blade effect d. Because of the slipstream effect
21. Choose the most correct answer from the options below. As a coarse blade pitch is efficient at cruising speeds, why should a pilot ever choose to select fine pitch?
a. In order to minimise fuel consumption
b. Because of noise limitations on climbing away from the airfield over built up areas
c. In order to increase engine RPM to the most fuel efficient level d. In order to optimise the aircraft’s performance on take-off
22. Which of the answers below is the most correct? What performance advantages does an aircraft possess if it is fitted with a fine pitch propeller? a. It will produce maximum thrust at higher cruising speeds
b. Its engine will be less likely to overheat in a climb, at high RPM and relatively low forward speed
c. The propeller will give optimal thrust for the take-off and initial climb d. It will be able to fly at high speeds without exceeding the maximum
23. What are the advantages of a constant-speed propeller? a. Cruise performance will be improved
b. Take off performance will be improved
c. The engine can never over-speed whatever the circumstances d. It provides an efficient blade angle of attack over a wide range of
airspeeds
24. What type of aircraft would most-likely be fitted with a fine, fixed-pitch propeller?
a. A touring aircraft b. A glider tug
c. A high-performance, military, turbo-prop training aircraft d. A turbo-prop passenger aircraft
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