WorksheetsCPD222Final
Total questions: 50
Worksheet time: 1hrs 10mins
In a glide descent at the optimum speed, the effect that increasing the nose-down pitch angle has on the glide distance is that:
(a) it increases
(b) it decreases
(c) it has no effect
(d) it increases but only in a headwind
Two identical aeroplanes are descending at idle thrust and the optimum angle of attack but at different masses. Which of the following statements is true?
(a) The heavier aeroplane will glide further.
(b) The lighter aeroplane will glide further.
(c) The vertical and forward speeds of the heavier aeroplane will be greater.
(d) There is no difference in their glide characteristics.
In a glide descent at the optimum gliding speed, if the pilot increases the pitch attitude the glide distance will:
(a) remain the same
(b) may increase or decrease depending on aeroplane type
(c) decrease
(d) increase
Which of the following factors will increase the glide time?
(a) increased aeroplane mass
(b) a headwind
(c) a tailwind
(d) decreased aeroplane mass
What effect does increased aeroplane mass have on a glide descent?
(a) None.
(b) Glide angle decreases.
(c) The lift/drag ratio decreases.
(d) The speed for the best angle of descent increases.
Which of the following statements for a glide descent at the maximum lift to drag ratio speed is correct?
(a) The mass of the aeroplane does not have any effect on the speed of descent.
(b) The higher the gross mass the greater is the speed for descent.
(c) The higher the gross mass the lower is the speed of descent.
(d) The higher the average temperature (OAT) the lower is the speed of descent.
What is the effect of an increased flap setting on the gradient and rate of climb?
(a) the gradient of climb increases and the rate of climb increases
(b) the gradient of climb increases and the rate of climb decreases
(c) the gradient of climb decreases and the rate of climb increases
(d) the gradient of climb decreases and the rate of climb decreases
The effect an increase of mass has on the values of the ROC and the climb speeds is:
(a) ROC decreases and the climb speeds remain the same
(b) ROC is unchanged and the climb speeds are unchanged
(c) ROC increases and the climb speeds increase
(d) ROC decreases and the climb speeds increase
How does the value of Vx vary with wind component?
(a) It increases in a headwind.
(b) It decreases in a tailwind.
(c) It is not affected by the wind component.
(d) It decreases in a headwind.
The greatest rate of climb at a constant mass:
(a) Decreases with increasing altitude because the thrust available decreases due to the decreased air density.
(b) Increases with increasing altitude because drag decreases due to the decreased air density.
(c) Increases with increasing altitude due to the higher TAS.
(d) Is independent of altitude.
Apart from lift, the forces that determine the angle of climb are:
(a) mass and drag only
(b) thrust and drag only
(c) mass and thrust only
(d) mass, drag and thrust
Vx and Vy with take-off flaps will be:
(a) higher than that for the clean configuration
(b) lower than that for the clean configuration
(c) same as that for the clean configuration
(d) changed so that Vx increases and Vy decreases compared with the clean configuration
The factors that will increase the ground distance travelled in a glide descent are:
(a) decreased aeroplane mass
(b) a tailwind
(c) a headwind
(d) increased aeroplane mass
The speed to obtain the minimum glide angle occurs at:
(a) Cl/Cdmax
(b) Clmax
(c) Cl/Cd2max
(d) Cl3/Cd2max
The critical Mach number of an aeroplane is increased by:
(a) swept wings
(b) vortex generators
(c) control deflection
(d) wing dihedral
In transonic flight the ailerons are less effective than in subsonic flight because:
(a) the air pressure is less behind the shockwave
(b) aileron deflection downward moves the shockwave forward
(c) aileron deflection only affects the air ahead of the shockwave
(d) aileron deflection only partially affects the pressure distribution around the wing
When flying at a constant IAS as the mass decreases the Mcrit:
(a) is independent of the angle of attack
(b) decreases
(c) increases
(d) remains constant
The flight regime between Mcrit and Mach 1.3 is the:
(a) transonic range
(b) supersonic range
(c) hypersonic range
(d) subsonic range
Mcrit is the free-stream Mach number that produces the first evidence of:
(a) local sonic flow
(b) buffet
(c) shockwave
(d) supersonic flow
In the case of a supersonic flow being retarded by a normal shockwave, the loss of total pressure can be minimized if the Mach number in front of the shockwave is:
(a) supersonic
(b) less than 1
(c) equal to 1
(d) small but still supersonic
When air has passed through a normal shockwave the Mach number is:
(a) less than before but still greater than 1
(b) equal to 1
(c) higher than before
(d) less than 1
The type of flow separation that occurs at the lowest angle of attack is the:
(a) shock stall
(b) high-speed stall
(c) low-speed stall
(d) deep stall
The two methods of increasing the critical Mach number are:
(a) thin aerofoils and wing dihedral
(b) positive cambering of the aerofoil and wing sweep back
(c) thick aerofoils and wing dihedral
(d) thin aerofoils and wing sweep back
Critical Mach number is the:
(a) speed at which there is supersonic airflow over the whole aeroplane
(b) the highest speed for which the aeroplane is certificated
(c) the highest speed without supersonic flow over any part of the aeroplane
(d) the speed at which there is subsonic airflow over all parts of the aeroplane
In the transonic range lift will decrease at the shock stall due to the:
(a) first appearance of a shockwave on the wing upper surface
(b) first appearance of the bow wave
(c) separation of the boundary layer at the shockwaves
(d) attachment of the shockwave on the wing trailing edge
The application of the area rule decreases:
(a) form drag
(b) wave drag
(c) skin friction
(d) induced drag
Which of the following statements regarding the normal shockwave is correct?
(a) The airflow changes from supersonic to subsonic.
(b) The airflow changes direction.
(c) The airflow changes from subsonic to supersonic.
(d) The airflow expands when passing the aerofoil.
The speed of sound is affected by the air:
(a) temperature
(b) density
(c) pressure
(d) humidity
Mach number is the ratio between the:
(a) TAS and the local speed of sound
(b) TAS and the speed of sound at sea level
(c) IAS and the local speed of sound
(d) IAS and the speed of sound at sea level
The movement of the CP when accelerating from subsonic to supersonic flight is:
(a) forward
(b) to a position near the leading edge
(c) to a position near the trailing edge
(d) to the midchord position
The critical Mach number can be increased by:
(a) increased aspect ratio
(b) swept wings
(c) positive wing dihedral
(d) a T-tail
The speed of the local airflow after passing through a normal shockwave is:
(a) more than the speed of sound
(b) equal to the speed of sound
(c) initially more than the speed of sound then decreasing to less than the speed of sound
(d) less than the speed of sound
When operating in the transonic range, lift decreases when the shock stall occurs because:
(a) of the appearance of the bow wave
(b) of the shockwave attaching itself to the trailing edge of the wing
(c) of the separation of the boundary layer at the shockwave
(d) the speed has reached Mcrit
The speed at which the shockwave moves over the ground is equal to:
(a) the aeroplane’s TAS
(b) the aeroplane’s groundspeed
(c) the speed of sound at the aeroplane’s cruising level
(d) the speed of sound at ground level
The effect that a shock stall has on a swept-wing aeroplane is that it:
(a) pitches nose-up
(b) pitches nose-down
(c) has no effect on longitudinal stability
(d) increases longitudinal stability
In the transonic flight regime aft movement of the CP:
(a) improves the directional stability
(b) improves the static longitudinal stability
(c) improves the static lateral stability
(d) improves the sideslip stability
The Mach trimmer corrects for:
(a) movement of the centre of pressure
(b) movement of the centre of gravity
(c) pitch-up
(d) shockwave drag
The speed range between the high-speed buffet and the low-speed buffet:
(a) decreases during a constant IAS descent
(b) increases during a constant IAS climb
(c) increases during a descent at a constant IAS
(d) remains constant irrespective of altitude
The blade angle of attack of a fixed-pitch propeller increases when:
(a) forward speed and RPM decrease
(b) RPM increases and forward speed decreases
(c) forward speed and RPM increase
(d) forward speed increases and RPM decreases
Why is a propeller blade twisted from root to tip?
(a) To ensure that the root produces the greatest thrust.
(b) To ensure that the tip produces the greatest thrust.
(c) Because the blade angle of attack is dependent at any point on the ratio of the rotational speed to the TAS.
(d) Because the blade angle of attack is dependent at any point on the ratio of the rotational speed to the propeller angular velocity.
During a glide descent of a constant-speed propeller aeroplane at idle thrust and a constant speed, if the RPM lever is pulled back the propeller pitch will:
(a) increase and the rate of descent will decrease
(b) increase and the rate of descent will increase
(c) decrease and the rate of descent will decrease
(d) decrease and the rate of descent will increase
Gyroscopic precession of the propeller is induced by:
(a) pitching and rolling
(b) increasing RPM and yawing
(c) increasing RPM and rolling
(d) pitching and yawing
Which of the following statements regarding propeller drag is correct.
An engine failure can result in the drag of (i) a windmilling propeller and (ii) a nonrotating propeller.
(a) (i) is equal to (ii)
(b) (ii) is larger than (i)
(c) impossible to say which is the largest
(d) (i) is larger than (ii)
The advantages of increasing the number of blades on a propeller is:
(a) decreased efficiency
(b) increased noise
(c) increased vibration
(d) increased power absorption
During a glide with idle thrust at a constant IAS if the propeller pitch is decreased the lift/drag ratio will:
(a) decrease
(b) increase
(c) remain the same
(d) increase when the CSU activates
The drag of a windmilling propeller compared with that of a stationary propeller is that:
(a) the windmilling propeller has less drag
(b) the windmilling propeller has more drag
(c) they are the same
(d) it is impossible to determine
During a constant IAS climb, in a normal atmosphere, with a fixed-pitch propeller the angle of attack of the propeller:
(a) decreases
(b) remains the same
(c) diminishes to zero
(d) increases
In level flight with the port engine inoperative and wings level the correct turn and slip indication is:
(a) turn indicator neutral and slip indicator neutral
(b) turn indicator displaced left and slip indicator displaced left
(c) turn indicator displaced left and slip indicator displaced right
(d) turn indicator displaced right and slip indicator displaced left
If the speed exceeds Va by a few knots:
(a) the aeroplane cannot stall
(b) a high-speed warning horn will sound
(c) there will be structural failure on entering a turn
(d) permanent damage to the airframe may occur if the elevators are fully deflected
The advantage of rear-mounted engines over wing-mounted engines is:
(a) the wing is less susceptible to flutter
(b) lighter wing construction reducing the mass
(c) thrust changes have less affect on longitudinal control
(d) easier maintenance access
