WorksheetsPOF 2
Total questions: 50
Worksheet time: 25mins
The term angle of attack is defined as:
the angle between the relative airflow and the horizontal axis
the angle between the wing chord line and the relative airflow
the angle that determines the magnitude of the lift force
the angle between the wing and tailplane incidence
An aircraft carries out a given journey, on two separate days. On both days, the pilot flies at an indicated airspeed of 120 knots. On the first day, the air density is greater than on the subsequent day. How will the forces of Lift and Drag acting on the aircraft compare on the two days?
On the first day both Lift and Drag will be less than on the subsequent day
On the first day the Lift will be greater and Drag will be less than on the subsequent day
On the first day the Lift will be less and Drag will be greater than on the subsequent day
The forces of Lift and Drag acting on the aircraft will remain unchanged
As airspeed increases, induced drag:
Increases
Decreases
is dependent on the weight of the aircraft
remains unchanged
As airspeed increases induced drag______, parasite drag and total drag __
increases increases increases
increases decreases increases then decreases
decreases decreases decreases
decreases increases decreases then increases
By changing the Angle of Attack of a wing, the pilot can control the aeroplane's:
lift and airspeed, but not drag
lift, gross weight and drag
lift, airspeed and drag
lift and drag, but not airspeed
That portion of the aircraft's total drag created by the production of lift is called;
arasite drag, which is greatly affected by changes in airspeed
induced drag, which is not affected by changes in airspeed
induced drag, which is greatly affected by changes in airspeed
parasite drag, which is inversely proportional to the square of the airspeed
If the Indicated Air Speed of an aircraft is increased from 50 kt to 100 kt, parasite drag will be:
four times greater
six times greater
two times greater
one quarter as much
Resistance, or skin friction, due to the viscosity of the air as it passes along the surface of a wing, is a type of:
induced drag
form drag
parasite drag
interference drag
How do Lift and Parasite Drag vary with airspeed?
lift and Parasite Drag both decrease as the square of the airspeed
lift decreases as the square of the airspeed while Parasite Drag increases as the square of the airspeed
lift increases as the square of the airspeed while Parasite Drag decreases as the square of the airspeed
lift and Parasite Drag both increase as the square of the airspeed
Parasite drag varies with:
the square of the airspeed
CL max
the airspeed
the weight of the aircraft, only
Choose one of the four options below to make an accurate statement. As airspeed increases:
induced drag increases
induced drag is unaffected
form drag decreases
induced drag decreases
Which of the following is the cause of wing tip vortices?
air spilling from the top surface to the bottom surface at the wing tip
air spilling from the bottom surface to the top surface at the wing tip
the increased form drag at the wing tip
the increased parasite drag at the wing tip
Wing tip vortices are caused by unequal pressure distribution on the wing which results in airflow from:
bottom to top round the trailing edge
top to bottom round the trailing edge
bottom to top round the wingtip
top to bottom round the wingtip
Which of the following is the correct formula for drag?
1 /2pV2 CL S
1 /2prV(CD) 2 S
1 /2p 2V CD S
CD 1 /2.pV2S
Choose the option below which best describes aircraft drag considerations as True Air Speed increases:
parasite drag decreases and induced drag increases
parasite drag increases and induced drag increases
parasite drag decreases and induced drag decreases
parasite drag increases and induced drag decreases
In straight and level flight which of the following is correct? (L/D = Lift/Drag ratio)
L/D is maximum at the speed for minimum total drag
L/D decreases with increasing lift
L/D is maximum when lift equals weight
L/D is maximum when lift equals zero
If, in level flight, the airspeed decreases below that for maximum Lift / Drag. the effect will be that:
drag decreases because of lower induced drag
drag increases because of increased induced drag
drag increases because of increased parasite drag
drag decreases because of lower parasite drag
How does an aircraft's all-up weight affect its best power-off glide angle, in still air?
The best glide angle will be shallower
The best glide angle will be steeper
The best glide angle will not be affected
It is advisable not to carry out a power-off glide at maximum all-up weight
An aircraft's glide angle is solely a function of:
Its lift/drag ratio
Its all-up weight
The aircraft's state of trim.
The position of the C of G
Which of the following light aircraft performance criteria are achieved at L/D MAX
Endurance will be at a maximum
Angle of climb will be at a maximum
Service ceiling will be highest
Best rate of climb and maximum cruising range will be achieved
Choose the correct statement option below:
Weight and mass are conceptually the same.
Weight and mass are both forces.
Weight and mass are two different concepts; weight is a force and mass is a quantity of matter.
The weight and mass of a given body will be equal only in deep space.
Choose the correct statement option below
The scientific unit of mass is the Newton.
The scientific unit of force is the kilogram
The scientific unit of force is the meter per second2
The scientific unit of mass is the kilogram
The weight of an aircraft is:
The force acting on the aircraft's mass and directed towards the center of the Earth.
The same as the aircraft's mass
The mass of the aircraft when the aircraft is assumed to have zero weight.
The force acting on the aircraft to accelerate it in the horizontal plane
Choose the correct statement option below
A body always possesses the same mass and weight whatever the strength of the gravitational field.
The mass of a body is dependent on the strength of the gravitational field in which the body is situated.
A body always possesses the same mass but in zero gravity will have no weight.
The weight of a body is independent of the strength of the gravitational field in which the body is situated.
Choose the correct equation below.
weight (Newtons) = mass (kg) x linear acceleration (m/s2 )
weight (Newtons) = mass(kg) x acceleration due to gravity (m/s2 )
weight (kg) = force (Newtons) x acceleration (m/s2 )
weight (Newtons) = mass (kg)
On Earth:
weight (Newtons) = mass(kg) x linear acceleration (m/s2 )
weight (Newtons) = mass (kg) * 32 m/s2
weight (Newtons) = mass (kg) x 9.81 m/s2
weight (Newtons) = mass (kg) * m/s2
On the moon:
the weight of a body will be approximately 1/6 of its weight on the Earth.
the weight of a body will be approximately 6 times its weight on the Earth.
the weight of a body will be the same as its weight on the Earth
the mass of a body will be approximately 1/6 of its mass on the Earth.
When considering the linear acceleration of a body under the action of a given force:
It is the body's weight that will determine the magnitude of the acceleration.
Neither the body's mass nor its weight affects the magnitude of the acceleration.
It is the body's mass that will determine the magnitude of the acceleration,
A force cannot cause a linear acceleration
When considering lifting a body in a gravitational field:
It is the body's mass which is crucial to the consideration.
Neither a body's mass nor its weight affects the consideration.
A body of finite weight cannot be lifted in a gravitational field
It is the body's weight which is crucial to the consideration.
Despite the difference in concepts between weight and mass, weight may be expressed in kilograms on Earth because:
In a constant gravitational field mass is always equal to weight.
Given that the acceleration due to gravity is constant at 9.81 m/s2 , mass is directly proportional to weight, and, therefore, weighing devices may be calibrated to read mass in kilograms
In a constant gravitational field there is no difference between mass and weight.
In a constant gravitational field mass and weight have no meaning
A propeller blade is twisted along its length in order to:
give a progressively increasing blade angle from root to tip
give a progressively increasing angle of attack from root to tip when the propeller is rotating
compensate for the decreasing linear speed of the blade from root to tip
maintain the most efficient angle of attack along the whole length of the propeller blade when the propeller is rotating
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
Increases angle of attack
decreases geometric pitch
increases effective pitch
decreases angle of attack
As an aircraft with a variable-pitch, constant-speed propeller accelerator, along the runway:
the angle of attack will decrease and the engine RPM remain constant
the blade pitch angle increases, maintaining a constant angle of attack and constant RPM
the angle of attack will remain constant and the engine RPM will increase
the linear velocity of the propeller tip will gradually decrease
In a dive, with the throttle setting constant, the engine RPM of an aircraft fitted with a fixed-pitch propeller will:
decrease as the airspeed increases
remain constant whatever the airspeed
increase if the airspeed is allowed to increase
decrease as long as the throttle setting is not changed
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:
left roll and right yaw during take off
left roll and left yaw during take off
right roll and right yaw during take off
left yaw and right roll during take off
Which of the following combinations will decrease the angle of attack of a fixed pitch propeller blade?
Increased TAS and increased RPM
Increased TAS and decreased RPM
Decreased TAS and decreased RPM
Decreased TAS and increased RPM
Which of the following combinations will increase the angle of attack of a fixed pitch propeller blade?
increased TAS and increased RPM
increased TAS and decreased RPM
Decreased TAS and increased RPM
Decreased TAS and decreased RPM
The advantage of a constant speed propeller over a fixed pitch propeller is that:
a greater maximum thrust is available
a higher maximum efficiency is attained
more blade surface area is made available
optimal efficiency is achieved over a wide speed range
The angle of attack of a fixed, coarse-pitch propeller on a touring light aircraft:
will be lower during the take-off run than in flight
will be optimal in all flight conditions
will be most efficient at the cruising speeds published in the pilot's operating manual
will decrease with decreasing airspeed at constant engine RPM
A propeller blade is twisted from root to tip:
to provide maximum thrust at the root
to provide maximum thrust at the tip
so that propeller efficiency remains high, at any engine RPM
so that thrust remains approximately constant along the whole length of the propeller blade, at any engine RPM
The angle of attack of a fixed-pitch propeller designed for cruising flight is:
optimal for steady cruising flight only
increases with an increase in TAS
decreases with an increase in RPM
will always be positive in a power off glide
Propeller-blade angle of attack is the angle between the blade chord line and the:
plane of rotation of the propeller
aeroplane's gradient of climb
the airflow relative to the propeller
helix angle
What is the purpose of increasing the number of propeller blades?
To reduce noise
To improve power absorption
To increase the efficiency of the variable pitch mechanism
To enable a longer undercarriage to be fitted
What would be the gyroscopic effect of a clockwise rotating propeller (viewed from the pilot's seat) on a single-engine, tailwheel aircraft as it raises its tail during the takeoff run?
The aircraft would yaw to the right
The aircraft would yaw to the left
The aircraft would roll to the right
The aircraft would roll to the left
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?
Weight on left wheel decreased, weight on right wheel increased
Weight on left wheel increased, weight on right wheel remain constant
Weight on left wheel increased, weight on right wheel decreased
Weight on right wheel increased, weight on left wheel remain constant
Which of the following definitions of propeller parameters is correct?
Blade Angle is the angle between chord line and the relative airflow
Critical tip speed is the propeller speed at which there is a risk of the flow separating at some part of the propeller
Blade angle of attack is the angle between the blade chord line and propeller's plane of rotation
Geometric pitch is the theoretical distance that the propeller travels forward in one rotation
Which of the following gives the most correct explanation of why a propeller blade angle decreases from root to tip?
To compensate for the change in blade cross section from root in tip
To provide increased thrust at the root
To provide increased thrust at the tip
To compensate for the increase in rotational velocity from root to tip.
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?
Because a change in airspeed causes a change in inlet manifold pressure which affects engine power output
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
Because of the asymmetric blade effect
Because of the slipstream effect
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?
In order to minimize fuel consumption
Because of noise limitations on climbing away from the airfield over built up areas
in order to increase engine RPM to the most fuel efficient level
In order to optimize the aircraft's performance on take-off
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?
It will produce maximum thrust at higher cruising speeds
Its engine will be less likely to overheat in a climb, at high RPM and relatively low forward speed
The propeller will give optimal thrust for the take-off and initial climb
it will be able to fly at high speeds without exceeding the maximum permissible engine RPM
