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Worksheetsatppof
Total questions: 252
Worksheet time: 2hrs 6mins
Regarding a positively cambered aerofoil section, which statement is correct? 1) The angle of attack has a negative value when the lift coefficient equals zero. 2) A nose up pitching moment exists when the lift coefficient equals zero.
1) incorrect, 2) incorrect.
1) correct, 2) correct.
1) incorrect, 2) correct.
1) correct, 2) incorrect.
When a turn is initiated, adverse yaw is:
the tendency of an aeroplane to yaw in the same direction of turn due to the different wing speeds.
a momentary yawing motion opposite to the turn due to an incorrect differential aileron movement.
the tendency of an aeroplane to yaw in the opposite direction of turn mainly due to the difference in induced drag on each wing.
the tendency of an aeroplane to yaw in the opposite direction of turn mainly due to the difference in aileron form drag.
In which phase of the take-off is the aerodynamic effect of ice located on the wing leading edge most critical?
The take-off run.
The last pan of the rotation.
All phases are equally important.
During climb with all engines operating.
The twisting of a propeller blade from root to tip has been made to:
ensure its optimum thrust is always achieved at take-off.
prevent excessive stress at the blade tip at high RPM.
provide a constant angle of attack from root to tip.
provide its greatest thrust toward the blade root.
In straight and level flight at a speed of 1.3 Vs, the lift coefficient, expressed as a percentage of its maximum (CLMAX), would be:
169%
130%
59%
77%
If the propeller pitch of a wind milling propeller is decreased during a glide at constant lAS the propeller drag in the direction of flight will
decrease and the rate of descent will decrease.
increase and the rate of descent will decrease.
increase and the rate of descent will increase.
decrease and the rate of descent will increase.
Low speed pitch-up can be caused by a significant thrust:
decrease with engines located on the rear fuselage.
increase with podded engines located beneath a low-mounted wing.
decrease with podded engines located beneath a low-mounted wing.
increase with engines located on the rear fuselage.
Which statement about propeller noise is correct? 1) Propeller noise increases when the blade tip speed increases. 2) For a given engine and propeller blade shape, a decrease in the number of propeller blades allows for a reduction in propeller noise.
1) is incorrect, 2) is correct.
1) is correct, 2) is correct.
1) is correct, 2) is incorrect.
1) is incorrect, 2) is incorrect
The correct sequence of cross-sections representing propeller blade twist is:
sequence 1.
sequence 2.
sequence 4.
sequence 3.
Considering subsonic incompressible airflow through a Venturi, which statement is correct? 1) The dynamic pressure in the throat is the same as in the undisturbed airflow. 2) The total pressure in the throat is higher than in the undisturbed airflow.
1) is incorrect, 2) is correct.
1) is correct, 2) is incorrect.
1) is correct, 2) is correct.
1) is incorrect, 2) is incorrect
During the retraction of the flaps at a constant angle of attack the aeroplane starts to: (Note: all other factors of importance being constant)
bank.
sink suddenly.
climb.
yaw.
The stall speed in a 60° banked rurn increases by the following factor:
1.41
1.07
1.30
2.00
When an aeroplane enters ground effect:
the effective angle of attack is decreased.
the induced angle of attack is increased.
the lift is increased and the drag is decreased.
drag and lift are both reduced.
If the aspect ratio of a wing increases whilst all other relevant factors remain constant, the critical angle of attack will:
remain constant only for a wing consisting of symmetrical aerofoils
increase
remain constant
decrease
Asymmetric propeller blade effect is mainly induced by:
large angles of yaw.
large angles of climb.
the inclination of the propeller axis to the relative airflow.
high speed.
Which of these statements about the gust load factor on an aeroplane are correct or incorrect? 1) When the wing area decreases, the gust load factor decreases. 2) When the EAS decreases, the gust load factor decreases.
1) is correct, 2) is incorrect.
1) is incorrect, 2) is correct.
1) is correct, 2) is correct.
1) is incorrect, 2) is incorrect
Regarding the lift formula, if airspeed doubles, lift will:
be 4 times greater.
also double.
not change.
halve.
In a steady, level, co-ordinated turn:
the radius of turn depends only upon load factor
the rate of turn depends upon the TAS and angle of bank.
the radius of turn depends upon the weight and load factor.
the rate of turn depends upon the weight, TAS and angle of bank
Which statement is correct? 1) Propeller gyroscopic effect occurs during flight at constant aeroplane attitude. 2) Propeller gyroscopic effect is most noticeable during low speed flight at low propeller RPM.
1) is incorrect, 2) is correct.
1) is correct, 2) is correct.
1) is incorrect, 2) is incorrect
1) is correct, 2) is incorrect.
The point where a laminar boundary layer becomes turbulent is called:
the separation point.
the transition point.
the critical point.
the deflection point.
The sonic boom of an aeroplane flying at supersonic speed is created by:
aerodynamic heating.
shock waves around the aeroplane.
the centre of pressure, which is moving aft on the aerofoil.
the expansion flow behind the aeroplane
"Tuck under" is caused by (i) movement of the centre of pressure (CP) of the wing nd (ii) change of the downwash angle at the location of the stabilizer.
i) forward; ii) increasing.
i) forward; ii) decreasing.
i) aft; ii) increasing.
i) aft; ii) decreasing.
Which of these statements about weight or mass is correct?
Mass = weight x volume.
In the 51 system the unit of measurement for weight is the kilogram.
The mass of an object is independent of the acceleraoon due to gravity.
The weight of an object is independent of the acceleration due to gravity .
A laminar boundary layer is a layer, in which:
the vortices are weak.
the velocity is constant.
the temperature varies constantly.
no velocity components exist normal to the surface.
The centre of gravity moving aft will:
increase the elevator up effectiveness.
decrease the elevator up effectiveness.
not affect the elevator up or down effectiveness.
increase or decrease the elevator up effectiveness, depending on wing location.
An aeroplane in straight and level flight at 100 kts is subjected to a sudden disturbance in speed. Assuming the angle of attack remains constant initially and the load factor reaches a value of 1.44:
The speed will have decreased by 10 kts.
The speed will have increased by 10 kts.
The speed will have increased by 20 kts.
The speed will have decreased by 20 kts.
Assuming zero wind, an aeroplane in a straight steady glide will achieve the minimum glide angle at:
the highest altitude.
the lowest mass.
(CL/CD)MAX
(CL/CD)MIN
Which of the following statements is correct? 1) When the critical engine fails during take-off the speed VMCL can be limiting. 2) The speed VMCL is always limited by maximum rudder deflection.
1) is incorrect, 2) is incorrect
1) is correct, 2) is correct.
1) is correct, 2) is incorrect.
1) is incorrect, 2) is correct.
Considering subsonic incompressible airflow through a Venturi, which statement is correct? 1) The dynamic pressure in the throat is lower than in the undisturbed airflow. 2) The total pressure in the throat is lower than in the undisturbed airflow.
1) is correct, 2) is correct
1) is incorrect, 2) is incorrect
1) is correct, 2) is incorrect
1) is incorrect, 2) is correct
What is the approximate value of the lift of an aeroplane at a gross weight of 50 000 N, in a horizontal coordinated 45° banked turn?
50 000 N
60 000 N
70 000 N
80 000 N
Which statement about propeller icing is correct? 1) Propeller icing increases blade element drag and reduces blade element lift. 2) Propeller icing reduces propeller efficiency.
1) is correct, 2) is correct.
1) is correct, 2) is incorrect.
1) is incorrect, 2) is correct.
1) is incorrect, 2) is incorrect
What happens if CG moves behind the aft limit?
Stick forces become excessive.
Lateral stability will be decreased.
Insufficient manoeuvre stability.
Longitudinal stability increases.
One method to compensate adverse yaw is a:
differential aileron.
balance tab.
anti balance tab.
balance panel.
If the maximum pull force acceptable is so lbs and the design limit load factor of the aircraft is 6g. what stick force/g must be achieved to permit the aircraft to be manoeuvred to its design load factor limit?
10 lbs/g.
8.33 lbs/g.
6 lbs/g.
5 lbs/g.
Which of these statements concerning propellers is correct?
The blade angle of a feathered propeller is approximately 0 degrees.
The blade angle of a feathered propeller is approximately 90 degrees.
A windmilling propeller causes less drag than a feathered propeller.
An unfeathered propeller causes less drag than a feathered propeller.
Induced drag is the result of:
propeller slipstream over the wing.
boundary layer separation on the aft portion of the wing.
aerodynamic interaction between aeroplane parts.
downwash generated by tip vortices.
Which statement about propeller noise is correct? 1) Propeller noise decreases when the blade tip speed increases. 2) For a given engine and propeller blade shape, an increase in the number of propeller blades allows for a reduction in propeller noise.
1) is incorrect, 2) is correct.
1) is incorrect, 2) is incorrect
1) is correct, 2) is correct.
1) is correct, 2) is incorrect.
With increasing altitude and constant lAS the static lateral stability (i) and the dynamic lateral/directional stability (ii) of an aeroplane with swept back wing will:
i) increase; ii) increase.
i) increase; ii) decrease.
i) decrease; ii) decrease.
i) decrease; ii) increase.
Which of these statements about wing sweepback are correct or incorrect? 1) Decreasing wing sweepback decreases MCRIT. 2) Decreasing wing sweepback increases the drag divergence Mach number.
1) is incorrect, 2) is correct.
1) is correct, 2) is incorrect.
1) is correct, 2) is correct.
1) is incorrect, 2) is incorrect
The total drag of a three dimensional wing consists of:
pressure drag, friction drag and parasite drag.
induced drag and interference drag.
induced drag and parasite drag.
parasite drag and pressure drag.
1. In a steep turn to the left, when using flight spoilers for roll assistance and at the same time for reducing the airspeed:
the right aileron will ascend, the left one will descend, the right spoiler will extend and the left one will retract.
the right aileron will descend, the left one will ascend, the right spoiler will extend and the left one will retract.
the right aileron will descend the left one will ascend the right spoiler will retract and the left one will extend.
the right aileron will ascend, the left one will descend, the right spoiler will retract and the left one will extend.
In a single engine aircraft with a clockwise rotating propeller (seen from behind), a left yaw is generated due to:
the torque effect.
the slipstream, striking the fin on the left side.
higher lift on the right wing.
higher helix angle.
In supersonic flight, all disturbances produced by an aeroplane are:
in front of the aeroplane.
very weak and negligible.
in between a conical area, depending on the Mach number.
outside the conical area depending on the Mach number.
The resistance, or skin friction, due to the viscosity of the air as it passes along the surface of the wing is pan of the:
induced drag.
form drag.
parasite drag.
interference drag.
Which of these statements about induced drag are correct or incorrect? 1) Induced drag decreases as angle of attack increases. 2) At constant load factor, induced drag increases with increasing aeroplane mass.
1) is incorrect, 2) is correct.
1) is correct, 2) is incorrect.
1) is correct, 2) is correct.
1) is incorrect, 2) is incorrect
Assuming no flow separation, which of these statements about the flow around an aerofoil as the angle of attack increases are correct or incorrect? 1) The stagnation point moves up. 2) The point of lowest static pressure moves forward.
1) is correct, 2) is correct.
1) is correct, 2) is incorrect.
1) is incorrect, 2) is correct.
1) is incorrect, 2) is incorrect.
With a L/D ratio of 9:1 and flying at 12000 ft the glide range in still air would be approximately:
15 NM
20 NM
14 NM
18 NM
Which statement, about the effects on drag of fitting external tip tanks to the wings of an aeroplane, is correct? 1) Parasite drag increases. 2) Induced drag decreases.
1) is correct, 2) is incorrect.
1) is incorrect, 2) is incorrect
1) is correct, 2) is correct.
1) is incorrect, 2) is correct.
Which of these statements about the gust load factor on an aeroplane are correct or incorrect? 1) When the mass increases, the gust load factor decreases. 2) When the altitude decreases, the gust load factor decreases.
1) is incorrect, 2) is incorrect
1) is incorrect, 2) is correct
1) is correct, 2) is correct
1) is correct, 2) is incorrect
Which of these statements concerning flight in turbulence is correct?
When encountering turbulence during flight, the speed should be adjusted to the design speed for maximum gust intensity VB.
Above VB the aeroplane can never be overstressed by a gust.
The load factor in turbulence may fluctuate above and below 1 and can even become negative.
In severe turbulence. speed should be reduced to approximately 1.2 VS.
Left rudder pedal input will cause a:
left yaw about the vertical axis and left roll about the longitudinal axis.
right yaw about the vertical axis and right roll about the longitudinal axis.
left yaw about the vertical axis and right roll about the longitudinal axis.
right yaw about the vertical axis and left roll about the longitudinal axis.
Which of these statements are correct or incorrect regarding a sideslip, with the elative airflow coming from the right, on an aeroplane that exhibits both directional and lateral stability? 1) The initial tendency of the nose of the aeroplane is to move to the right. 2) The initial tendency of the left wing is to move down.
1) is correct, 2) is correct.
1) is incorrect, 2) is correct.
1) is incorrect, 2) is incorrect
1) is correct, 2) is incorrect.
For a fixed-pitch propeller in flight at a given TAS, the blade angle of attack will:
remain constant if RPM increases.
increase if RPM decreases.
decrease if RPM decreases.
remain constant if RPM decreases.
MMO can be exceeded in a climb at a constant lAS because:
maintaining a constant lAS requires an increase in TAS.
as altitude increases the local speed of sound increases.
at reduced density the Mach meter will under read.
position error increases.
What changes in aircraft control must be made to maintain altitude while the airspeed is being decreased?
Increase the angle of attack to compensate for the decreasing lift
Increase the angle of attack to produce more lift than drag.
Decrease the angle of attack to compensate for the increasing drag.
Maintain a constant angle of attack until the desired airspeed is reached, then increase the angle of attack.
Which statement, about an aeroplane leaving ground effect at constant angle of attack, is correct? 1) The lift coefficient CL increases. 2) The induced drag coefficient CDi decreases.
1) is correct, 2) is incorrect.
1) is incorrect, 2) is incorrect
1) is correct, 2) is correct.
1) is incorrect, 2) is correct.
Which aeroplane behaviour will be corrected by a yaw damper?
Spiral dive.
Tuck under.
Dutch roll.
Buffeting.
Which of these statements about flutter are correct or incorrect? 1) Wing mounted engines extending ahead of the wing contribute to wing flutter suppression. 2) Excessive free play or backlash increases the speed at which control surface flutter occurs.
1) is incorrect, 2) is correct.
1) is incorrect, 2) is incorrect.
1) is correct, 2) is incorrect.
1) is correct, 2) is correct.
Assuming zero wind, an aeroplane with a L/D ratio of 25:1 would cover a distance of approximately _ for every 1000 ft of height lost during a straight steady glide.
4 NM
2.5 NM
25 NM
40 NM
Which statement about an aeroplane entering ground effect is correct? 1) The downwash angle remains constant. 2) The induced angle of attack decreases.
1) is incorrect, 2) is incorrect
1) is correct, 2) is incorrect.
1) is incorrect, 2) is correct.
1) is correct, 2) is correct.
Ignoring downwash effects on the tailplane, extension of Fowler-type flaps, will produce:
a nose-down pitching moment.
no pitching moment.
a nose-up pitching moment.
a force which reduces drag.
When Fowler type trailing edge flaps are extended at a constant angle of attack, the following changes will occur:
CL increases and CD remains constant.
CL increases and the centre of pressure moves forward.
CL and CD increase.
CD decreases and the centre of pressure moves aft.
Given: Aeroplane mass: 50 000 kg;Lift/Drag ratio: 12;Thrust per engine: 21 000 N;Assumed g: 10 m/s²;For a straight, steady, wings level climb of a four-engine aeroplane, the all engines climb gradient will be:
8.5%
4.3%
7.7%
6.0%
On an asymmetrical, single curve aerofoil, in subsonic airflow, at low angle of attack, when the angle of attack is increased, the centre of pressure will (assume a conventional transport aeroplane):
move forward.
move aft.
remain matching the airfoil aerodynamic centre.
remain unaffected.
Which of these variables are required to calculate drag using the drag formula?
Total pressure and wing area only.
Frontal wing area, density and wing loading.
Angle of attack, aspect ratio and dynamic pressure.
Dynamic pressure, drag coefficient and wing area.
Assuming ISA conditions and no compressibility effects, If an aeroplane maintains straight and level·night at the same angle of arrack at two different altitudes, the:
lAS at both altitudes is the same.
TAS at both altitudes is the same.
lAS is higher at the higher altitude.
TAS is lower at the higher altitude.
To hold a given sideslip angle and airspeed. increased geometric dihedral would:
reduce the stick force to zero.
have no effect on stick force.
decrease the stick force.
increase the stick force.
Which of these statements about the strength of wing tip vortices are correct or incorrect? 1) Assuming no flow separation, the strength of wing tip vortices increases as the angle of attack increases. 2) The strength of wing tip vortices is not affected by aspect ratio.
1) is correct, 2) is correct.
1) is correct, 2) is incorrect.
1) is incorrect, 2) is correct.
1) is incorrect, 2) is incorrect
Which of these statements about the pitching moment coefficient versus angle of attack lines in the annex is correct?
The horizontal part of line 2 illustrates static longitudinal instability.
Static longitudinal stability is greater at line 3 when compared with line 4 at low and moderate angles of attack.
In its curved part at high angles of attack line 2 illustrates increasing static longitudinal stability.
The CG position is further aft at line 4 when compared with line 1.
When the air is passing through a shock wave, the density will:
decrease and beyond a certain Mach number start increasing again.
decrease
stay constant.
increase
A jet transport aeroplane is in a straight climb at a constant lAS and constant weight. The operational limit that may be exceeded is:
VNE
VMO
MMO
VD
Which of these statements about an oblique shock wave are correct or incorrect? 1) The static temperature behind an oblique shock wave is lower than in from of it. 2) The static pressure behind an oblique shock wave is lower than in front of it.
1) is correct, 2) is correct.
1) is correct, 2) is incorrect.
1) is incorrect, 2) is correct.
1) is incorrect, 2) is incorrect
The bow wave will first appear at:
a free stream Mach number just below M = 1.
a free stream Mach number exactly equal to 1.
a free stream Mach number just above M = 1.
the critical Mach number.
In general jet transport aeroplanes with power assisted flight controls are fitted with an adjustable stabiliser instead of trim tabs on the elevator. This is because:
the pilot does not feel the stick forces at all.
an adjustable stabiliser is a more powerful means to generate the tail loads required for these kind of aeroplanes.
mechanical adjustment of trim tabs creates too many problems.
trim tab deflection increases VMO.
Which of these statements about flutter are correct or incorrect? 1) Aero-elastic coupling does not affect flutter characteristics. 2) Occurrence of flutter is independent of lAS.
1) is correct, 2) is incorrect.
1) is incorrect, 2) is incorrect
1) is incorrect, 2) is correct.
1) is correct, 2) is correct.
Which of these statements about an oblique shock wave are correct or incorrect? 1) The Mach number behind an oblique shock wave is higher than in front of it. 2) The total pressure behind an oblique shock wave is lower than in front of it.
1) is correct, 2) is correct
1) is incorrect, 2) is incorrect
1) is correct, 2) is incorrect
1) is incorrect, 2) is correct
A forward CG shift
decreases static longitudinal stability.
has no influence on static longitudinal stability.
increases longitudinal manoeuvrability.
decreases longitudinal manoeuvrability.
In twin engine aeroplanes with propellers turning clockwise as seen from behind:
the left engine produces a higher yaw moment if the right engine fails than vice versa.
the left engine is the critical engine.
the minimum control speed is determined by the failure of the right engine.
the right engine is the critical engine.
Given: Aeroplane mass: 50 000 kg; Lift/Drag ratio: 12; Thrust per engine: 28 000 N; Assumedg: 10 m/s²; For a straight, steady, wings level climb of a three-engine aeroplane, the one-engine-inoperative climb; gradient will be:
8.0%
9.7%
2.9%
8.5%
Assuming all bodies have the same cross-sectional area and are in motion, which body will have the highest pressure drag?
Body C.
Body A
Body D
Body B
Directional stability is the stability around the:
longitudinal axis.
lateral axis.
normal axis.
pitch axis.
The critical angle of attack for the flaps down configuration, compared to flaps up is:
greater.
smaller
unchanged
smaller or greater, depending on CG position
When an aircraft is flying at speeds above Mach 1, pressure disturbances from the aircraft will affect only the flow:
within the Mach cone.
in front of the Mach cone.
in front of the oblique shockwave.
in front ofthe normal shockwave.
Which of these statements about induced drag are correct or incorrect? 1) Induced drag increases as angle of attack decreases. 2) At constant load factor, induced drag increases with decreasing aeroplane mass.
1) is incorrect, 2) is incorrect
1) is correct, 2) is correct.
1) is correct, 2) is incorrect.
1) is incorrect, 2) is correct.
The contribution of the wing to the static longitudinal stability of an aeroplane:
is always negative.
depends on CG location relative to the wing aerodynamic centre.
depends on the wing location relative to the fuselage.
is positive if the wing has a positively cambered aerofoil section and the aerodynamic centre is ahead of the CG.
What is the most effective flap system?
Single slotted flap.
Split flap.
Plain flap.
Fowler flap.
Which of these statements about the gust load factor on an aeroplane are correct or incorrect? 1) When the wing area increases, the gust load factor decreases. 2) When the EAS increases, the gust load factor decreases.
1) is correct, 2) is correct.
1) is incorrect, 2) is correct.
1) is incorrect, 2) is incorrect
1) is correct, 2) is incorrect.
The relationship between induced drag and the aspect ratio is:
a decrease in the aspect ratio increases the induced drag.
there is no relationship.
induced drag = 1.3 aspea ratio value.
an increase in the aspect ratio increases the induced drag.
Given an aeroplane with a propeller turning anti-clockwise as seen from behind, the torque effect will tend to:
pitch the aeroplane nose down.
pitch the aeroplane nose up.
roll the aeroplane to the right.
roll the aeroplane to the left.
Which statement, about an aeroplane entering ground effect at constant angle of attack, is correct? 1) The lift coefficient CL decreases. 2) The induced drag coefficient CDi increases
1) is incorrect, 2) is correct.
1) is correct, 2) is correct.
1) is incorrect, 2) is incorrect
1) is correct, 2) is incorrect.
Which of the following (i) aerofoils and (ii) angles of attack will produce the lowest MCRIT values?
i) thick; ii) small
i) thick; ii) large
i) thin; ii) large
i) thin; ii) small
Comparing the differences between a horizontal trimmable stabiliser and an elevator trim tab, which of these statements are correct or incorrect? 1) An elevator trim tab is more suitable to cope with the large trim changes generated by the high lift devices on most jet transport aeroplanes. 2) A trim tab runaway causes less control difficulty.
1) is incorrect, 2) is correct.
1) is correct, 2) is correct.
1) is incorrect, 2) is incorrect
1) is correct, 2) is incorrect.
Speed brakes are devices used on large transport category aircraft:
for speed reduction during landing.
and are an old version of ami-block system.
to increase drag in order to maintain a steeper gradient of descent
used at high speeds for turning when a yaw damper is not installed.
Which statement about a propeller is correct? 1) Asymmetric blade effect increases when engine power is increased. 2) Asymmetric blade effect is independent of the angle between the propeller axis and the airflow through the propeller disc.
1) is correct, 2) is correct.
1) is incorrect, 2) is incorrect
1) is incorrect, 2) is correct.
1) is correct, 2) is incorrect.
If the propeller pitch of a windmilling propeller is increased during a glide at constant lAS the propeller drag in the direction of flight will:
decrease and the rate of descent will decrease.
increase and the rate of descent will decrease.
decrease and the rate of descent will increase.
increase and the rate of descent will increase.
One advantage of a movable-stabiliser system compared with an elevator trim system is that:
the systems complexity is reduced.
the struccure weighs less.
it leads to greater stability in flight.
it is a more powerful means of trimming.
Which statement about stick force per G is correct?
The stick force per G can only be corrected by means of elearonic devices (stability augmentation) in case of an unacceptable value.
The stick force per G increases, when centre of gravity is moved aft.
The stick force per G must have both an upper and lower limit in order to assure acceptable control characteristics.
If the slope of the force line becomes negative, generally speaking this is not a problem for control of an aeroplane.
Dihedral of the wing is:
the angle between the 0.25 chord line of the wing and the vertical axis.
the angle between the 0.25 chord line of the wing and the horizon.
the angle between the 0.25 chord line of the wing and the lateral axis.
the angle between the leading edge of the wing and the lateral axis.
Considering subsonic incompressible airflow through a Venturi, which statement is correct? 1) The dynamic pressure in the throat is higher than in the undisturbed airflow. 2) The total pressure in the throat is lower than in the undisturbed airflow.
1) is incorrect, 2) is incorrect
1) is correct, 2) is incorrect.
1) is correct, 2) is correct.
1) is incorrect, 2) is correct.
If TAS is kept constant, to maintain straight and level flight with reduced air density the angle of attack of an aircraft's wings must be:
increased
decreased
unaltered
increased to the critical angle of attack.
An aeroplane is performing a co-ordinated level turn with a constant bank angle. If the airspeed is increased the rate of turn will (i) and the load factor will (ii)
i) decrease; ii) decrease.
i) decrease; ii) not change.
i) increase; ii) increase.
i) increase; ii) not change.
How does positive camber of an aerofoil affect static longitudinal stability?
Negatively, because the lift vector rotates forward at increasing angle of attack
Positively, because the centre of pressure shifts rearward at increasing angle of attack
No effect, because camber of the aerofoil produces a constant pitch down moment coefficient, independent of angle of attack
Positively, because the lift vector rotates backward at increasing angle of attack.
A statically stable aeroplane:
is never dynamically stable.
is always dynamically stable.
can show positive. neutral or negative dynamic longitudinal stability.
will never show positive dynamic longitudinal stability. but always neutral dynamic longitudinal stability.
At MCRIT, a shockwave will appear first:
at the leading edge.
near to the point of maximum wing thickness.
at the trailing edge.
on the underside of the wing.
Which statement is correct? 1) The angle of attack of a positively cambered aerofoil has a negative value when the lift coefficient equals zero. 2) There is a nose down pitching moment about a positively cambered aerofoil when the lift coefficient equals zero.
1) is incorrect, 2) is correct.
1) is correct, 2) is incorrect.
1) is correct, 2) is correct.
1) is incorrect, 2) is incorrect
Comparing the differences between a horizontal trimmable stabiliser and an elevator trim tab, which statement is correct? 1) A stabiliser trim is less suitable for jet transport aeroplanes because of their large speed range. 2) A trim tab is a more powerful means of trimming.
1) is correct, 2) is correct.
1) is incorrect, 2) is incorrect
1) is correct, 2) is incorrect.
1) is incorrect, 2) is correct.
Considering subsonic incompressible airflow through a Venturi, which statement is correct? 1) The dynamic pressure in the throat is lower than in the undisturbed airflow. 2) The total pressure in the throat is higher than in the undisturbed airflow.
1) is correct, 2) is incorrect.
1) is incorrect, 2) is correct.
1) is incorrect, 2) is incorrect
1) is correct, 2) is correct.
Which of these statements about stall speed is correct?
Decreasing sweepback increases stall speed.
Decreasing sweepback decreases stall speed.
Decreasing wing anhedral decreases stall speed.
Increasing wing anhedral decreases stall speed.
Which of these statements about the gust load factor on an aeroplane are correct or incorrect? 1) When the slope of the lift versus angle of attack curve decreases, the gust load factor increases. 2) When the wing loading decreases. the gust load factor increases.
1) is correct, 2) is incorrect
1) is incorrect, 2) is correct
1) is correct, 2) is correct
1) is incorrect, 2) is incorrect
A rectangular wing, compared to other wing planforms, has a tendency to stall:
first at the leading edge, with progression outward toward the wing root and tip
first at the Wingtip, with the stall progression toward the wing root.
first at the wing root, with the stall progression towards the wing tip.
first at the semi-span centre, giving good aerodynamic stall warning.
During a short period oscillation, the altitude:
varies significantly, whereas during a phugoid it remains approximately constant.
varies significantly, as it does during a phugoid.
remains approximately constant, whereas during a phugoid it varies significantly.
remains approximately constant, as it does during a phugoid.
When the CG Is close to the forward limit:
the stalling speed is reduced.
the longitudinal stability is reduced.
very small forces are required on ttte control column to produce pitch.
very high stick forces are required in pitch because the aircraft is very stable
Propeller slip is the difference between the:
geometric pitch and the blade angle.
geometric pitch and the effective pitch.
plane of rotation and the aircraft's forward velocity.
RPM of the engine and the RPM of the propeller.
The speed for minimum glide angle occurs at an angle of attack that corresponds to (assume zero thrust):
(CL/CD²)MAX
CLMAX
(CL/CD)MAX
(CL³/CD²)MAX
Which of the following statements about a constant speed propeller is correct?
The blade angle increases with increasing aeroplane speed.
The propeller system keeps the aeroplane speed constant.
The RPM decreases with increasing aeroplane speed.
The selected RPM is kept constant by the manifold pressure.
The lift coefficient CL versus angle of attack curve of a positively cambered aerofoil section intersects the horizontal axis of the graph:
to the left of the origin.
at the origin.
nowhere.
to the right of the origin.
Which of the following statements concerning control is correct?
In general the maximum downward elevator deflection is larger than upward.
On some aeroplanes, the servo tab also serves as a trim tab.
Hydraulically powered control surfaces do not need mass balancing.
In a differential aileron control system the control surfaces have a larger upward than downward maximum deflection.
Propeller blade twist is the:
varying of the helix angle from the root to the tip of a propeller blade
angle between the relative airflow and the propeller blade's angle of attack.
angle between the blade angle and the direction of the flight of the aeroplane.
varying of the blade angle from the root to the tip of a propeller blade
Which of these statements about the strength of wing tip vortices are correct or incorrect? 1) Assuming no flow separation, the strength of wing tip vortices increases as the angle of attack decreases. 2) The strength of wing tip vortices increases as the aspect ratio increases.
1) is correct, 2) is correct.
1) is incorrect, 2) is correct.
1) is correct, 2) is incorrect.
1) is incorrect, 2) is incorrect
Which moments or motions interact in a Dutch roll?
Rolling and yawing.
Pitching and yawing.
Pitching and rolling.
Pitching and adverse yaw.
The parameters that can be read from the "parabolic polar'' curve of an aeroplane are the:
The aspect. rario of the wing and the induced drag coefficient.
The minimum rare of descent and the induced drag.
The induced drag and the parasite drag.
The minimum glide angle and the parasite drag coefficient.
One disadvantage of wing sweep back is:
that the critical Mach number is significantly lower.
a severe pitch down moment when the centre of pressure shifts forward.
the tendency of the wing root section to stall prior to the wingtip section.
the tendency of the wingtip section to stall prior to the wing root section.
An aeroplane has static directional stability if, when in a sideslip with the relative airflow coming from the left, initially the:
right wing tends to go down.
nose of the aeroplane tends to yaw right.
nose of the aeroplane tends to yaw left.
nose of the aeroplane does not move.
Considering subsonic incompressible airflow through a Venturi, which statement is correct? 1) The dynamic pressure in the undisturbed airflow is lower than in the throat.2) The total pressure in the undisturbed airflow is higher than in the throat.
1) is incorrect, 2) is correct.
1) is correct, 2) is correct.
1) is correct, 2) is incorrect.
1) is incorrect, 2) is incorrect
An aeroplane flying at 200 kts in straight and level flight is subjected 10 a disturbance that suddenly decreases the speed by 80 kcs. Assuming the angle of actack remains constant, the load factor will initially:
decrease to 0.36.
decrease to 0.50.
decrease to 0.60.
remain unchanged, since the angle of actack does not change.
Which of these statements about wing sweepback are correct or incorrect? 1) Increasing wing sweepback increases MCRIT· 2) Increasing wing sweepback increases the drag divergence Mach number.
1) is incorrect, 2) is correct.
1) is correct, 2) is correct.
1) is incorrect, 2) is incorrect
1) is correct, 2) is incorrect.
When flaps are deployed at constant angle of attack the lift coefficient will:
remain the same.
decrease
increase
vary as the square of lAS.
Which statement is correct about a spring tab?
At high lAS it behaves like a fixed extension of the elevator.
Its main purpose is to increase stick force per G.
At high lAS it behaves like a servo tab.
At low lAS it behaves like a servo tab.
During a climb at a constant lAS, the Mach number will:
remain constant.
decrease initially and increase subsequently.
increase
increase initially and remain constant subsequently.
As fuel is consumed during a level flight cruise at high level:
the angle of attack must be increased.
the stalling speed will increase.
the centre of pressure will move forward.
induced drag will decrease.
To cover the greatest distance when gliding, the gliding speed must be:
near to the stalling speed.
as high as possible within V limits.
minimum control speed.
the one that gives the lowest total drag.
Which statement about an aeroplane entering ground effect is correct?1) The downwash angle increases. 2) The induced angle of attack increases.
1) is correct, 2) is correct.
1) is incorrect, 2) is incorrect
1) is correct, 2) is incorrect.
1) is incorrect, 2) is correct.
An in-flight move of the CG of an aircraft further aft will:
Increase the angle of attack.
reduce the longitudinal stability.
increase the longitudinal stability.
have no effect on the longitudinal stability.
Assuming ISA conditions and a climb above the tropopause at constant Mach number and aeroplane mass, the:
TAS increases.
lAS decreases.
Iift coefficient decreases.
lift coefficient remains constant.
The forces of lift and drag on an aerofoil are, respectively, normal and parallel to the:
relative wind/airflow.
chord line.
longitudinal axis.
horizon.
A "slat" on a wing is:
A leading edge flap.
A split flap along the leading edge of the wing.
A leading edge device that causes some of the high energy air to flow over the upper surface of the wing.
Another expression for a Fowler flap.
The aerodynamic centre of a wing is the point relative to which:
the boundary layer changes from laminar to turbulent.
assuming no flow separation. the pitching moment coefficient does not change with varying angle of attack.
the velocity of the relative airflow is reduced to zero.
the aeroplane becomes longitudinally unstable when the CG is moved beyond it in an aft direaion.
The effect of Mach trim on stick forces for power operated controls:
Is to maintain the required stick force gradient.
Is to decrease the stick force gradient to ensure the pilot can manoeuvre the aircraft adequately when flying at a high transonic Mach number.
Is to decrease the stick force gradient to prevent the possibility of high speed stall.
A Mach trim system is not required If an aircraft has power operated controls.
Where on the curve in the diagram does the aeroplane exhibit static longitudinal instability?
The whole curve.
Point 2.
Part 1.
Part 3.
1. Which of these statements about the effect of wing sweep on center of pressure location are correct or incorrect? 1) The centre of pressure on a straight wing moves forward as the angle of attack approaches and exceeds the critical angle of attack. 2) When sweep back increases the center of pressure has an increased tendency to move aft as the angle of attack approaches and exceeds the critical angle of attack.
1) is incorrect, 2) is incorrect
1) is correct, 2) is correct.
1) is correct, 2) is incorrect.
1) is incorrect, 2) is correct.
Aileron reversal may be caused by:
the wing twisting and increasing incidence when the aileron is lowered.
the wing twisting and reducing incidence when the aileron is lowered.
the aileron being pushed in the reverse direction by aileron drag.
the wing twisting and reducing incidence when the aileron is raised.
At constant EAS, what is the effect on aerodynamic damping as height increases?
Damping in all axes is reduced.
Damping in pitch manoeuvres only is reduced.
Damping in roll is increased.
Damping in all axes is increased.
Considering subsonic incompressible airflow through a Venturi, which statement is correct? 1) The dynamic pressure in the undisturbed airflow is lower than in the throat. 2) The total pressure in the undisturbed airflow and in the throat is the same.
1) is correct, 2) is incorrect.
1) is incorrect, 2) is incorrect
1) is incorrect, 2) is correct.
1) is correct, 2) is correct.
VMCA is the minimum speed at which directional control can be maintained when, amongst others: 1) maximum take-off thrust was set and is maintained on the remaining engines. 2) a sudden engine failure occurs on the most critical engine. 3) flaps are in any position. 4) the gear is either up or down. 5) the aeroplane is either in or out of ground effect. The combination that regroups all of the correct statements is:
1, 2, 4
2, 3, 5
3, 4, 5
1, 2
Just above the critical Mach number the first evidence of a shock wave will appear at the:
upper side of the wing.
lower side of the wing.
leading edge of the wing.
trailing edge of the wing.
Which statement is correct regarding the gyroscopic effect of a clockwise rotating propeller on a single engine aeroplane? 1) Pitch up produces right yaw. 2) Right yaw produces pitch down.
1) is correct, 2) is correct.
1) is incorrect, 2) is incorrect.
1) is correct, 2) is incorrect
1) is incorrect, 2) is correct.
Flutter of control surfaces is:
divergent oscillatory motion of a control surface caused by the interaction of aerodynamic, inertia and friction forces.
a divergent oscillatory motion of a control surface caused by the interaction of aerodynamic forces, inertia forces and the stiffness of the structure.
aileron reversal.
the accelerated stall of a wing.
Given: Aeroplane mass: 50 000 kg; Lift/Drag ratio: 12; Thrust per engine: 60 000 N; Assumedg: 10 m/s²; For a straight, steady, wings level climb of a twin engine aeroplane, the one-engine-inoperative climb gradient will be:
3.7%
15.7%
14%
11 .7%
1. Vortex generators on the upper side of the wing:
increase critical Mach number.
increase wave drag.
decrease wave drag.
decrease critical Mach number.
As angle of arrack is increased on a conventional low speed aerofoil at low subsonic speeds, flow separation normally starts on the:
upper surface near the leading edge.
upper surface near the trailing edge.
lower surface near the leading edge.
lower surface near the trailing edge.
If angle of attack is increased beyond the critical angle of attack, the lift coefficient and the stagnation point moves .
decreases; rearward
increases; rearward
decreases; forward
increases; forward
Assuming standard atmospheric conditions, in order to generate the same amount of lift as altitude is increased, an aeroplane must be flown at:
a higher TAS for any given angle of attack.
the same TAS regardless of angle of attack.
a lower TAS and a lower angle of attack.
a lower TAS for any given angle of attack.
The lift coefficient CL versus angle of attack curve of a negatively cambered aerofoil section intersects the vertical axis of the graph:
below the origin.
above the origin.
nowhere
at the origin.
For a given elevator deflection, aeroplane longitudinal manoeuvrability decreases when:
the CG moves aft.
flaps are retracted at constant lAS.
the CG moves forward.
lAS increases.
Which of these statements about an oblique shock wave are correct or incorrect? 1) The Mach number behind an oblique shock wave is lower than in front of it. 2) The total pressure behind an oblique shock wave is lower than in front of it.
1) is incorrect, 2) is incorrect
1) is correct, 2) is correct.
1) is incorrect, 2) is correct.
1) is correct, 2) is incorrect.
Given: Aeroplane mass: 50 000 kg; Lift/Drag ratio: 12; Thrust per engine: 20 000 N; Assumed g: 10 m/s²; For a straight, steady, wings level climb of a four-engine aeroplane. the all engines climb gradient will be:
4.3%
7.7%
60%
8.5%
Stall speed (lAS) varies with:
altitude (below approximately 10 000 ft)
weight
density
temperature
Considering subsonic incompressible airflow through a Venturi, which statement is correct? 1) The static pressure in the throat is higher than in the undisturbed airflow. 2) The speed of the airflow in the throat is the same as in the undisturbed airflow.
1) is correct, 2) is correct.
1) is correct, 2) is incorrect.
1) is incorrect, 2) is correct.
1) is incorrect, 2) is incorrect
Two identical aeroplanes A and B, with the same mass, are flying steady level co-ordinated 20° bank turns. If the TAS of A is 130 kts and the TAS of B is 200 kts:
the turn radius of A is greater than that of B.
the load factor of A is greater than that of B.
the rate of turn of A is greater than that of B.
the lift coefficient of A is less than that of B.
Which direction from the primary control surface does an elevator adjustable trim tab move when the control surface is moved?
Same direction.
Opposite direction.
In the same direction at high speeds to increase the stick force, but in the opposite direction at low speed.
Remains fixed for all positions.
Considering subsonic incompressible airflow through a Venturi, which statement is correct? 1) The static pressure in the throat is lower than in the undisturbed airflow. 2) The speed of the airflow in the throat is the same as in the undisturbed airflow.
1) is correct, 2) is correct
1) is incorrect, 2) is correct
1) is incorrect, 2) is incorrect
1) is correct, 2) is incorrect
What is the effect on an aeroplane's characteristics of extending Fowler flaps to their fully extended position?
CD remains constant for a given angle of attack.
wing area and camber increase.
wing area remains constant but camber increases.
CLMAX occurs at a higher angle of attack.
Which of these statements about the supersonic speed range is correct?
The airflow everywhere around the aeroplane is supersonic.
The supersonic speed range starts at a Mach number below M = 1 and extends to Mach numbers above M = 1.
The airflow around the aeroplane is transonic.
The supersonic speed range starts at M = 1 and ends at MCRIT.
Which statement is correct?
During a phugoid altitude varies significantly, but during a short period oscillation it remains approximately constant
During both a phugoid and a short period oscillation altitude remains approximately constant.
During both a phugoid and a short period oscillation altitude varies significantly.
During a phugoid al titude remains approximately constant, but during a short period oscillation it varies significantly.
If the increased downwash at the tail plane due to lowering (extending) trailing edge flaps is considered in isolation:
a nose up pitching moment will be generated.
a nose down pitching moment will be generated.
the direction of the pitch change will depend on the initial direaion of the tall load.
tall plane angle of attack will be decreased, causing a nose down pitching moment.
Which statement is correct? 1) A stick pusher activates at a higher angle of attack than a stick shaker. 2) A stick pusher prevents the pilot from increasing the angle of attack further
1) is correct, 2) is correct
1) is correct, 2) is incorrect
1) is incorrect, 2) is correct
1) is incorrect, 2) is incorrect
Which of the following statements about static lateral and directional stability is correct?
The effects of static lateral and static directional stability are completely independent of each other because they take place about different axis.
An aeroplane with an excessive static directional stability in relation to its static lateral stability, will be prone to spiral dive (spiral instability).
An aeroplane with an excessive static directional stability in relation to its static lateral stability, will be prone to Dutch roll.
Static directional stability can be increased by installing more powerful engines.
Which of the following wing planforms produces the lowest induced drag? (assume zero wing twist)
Rectangular
Elliptical
Tapered
Circular
An engine failure can result in a windmilling (i) propeller and a non-rotating (ii) propeller. Which statement about propeller drag is correct?
ii) is larger than i).
i) is equal to ii).
i) is larger than ii).
Impossible to say which one is larger.
Which of these statements about stall speed is correct?
Decreasing wing anhedral decreases stall speed.
Increasing wing anhedral decreases stall speed.
Increasing forward sweep decreases stall speed.
Increasing forward sweep increases stall speed.
Flutter sensitivity of an aeroplane wing is reduced by:
a high speed (lAS)
locating the engine ahead of the torsional axis of the wing.
empty tanks near the wing tip.
a low torsion stiffness in relation to the bending stiffness.
When comparing the properties of laminar and turbulent boundary layers, which of the following statements is correct?
Separation point will occur earlier in the turbulent layer.
Friction drag will be equal in both types of layers.
Friction drag is lower in the turbulent layer.
Friction drag is lower in the laminar layer.
Upon extension of a wing spoiler, if the angle of attack remains constant:
both CL and CD are increased.
CD is increased and CL is decreased.
CL is decreased, while CD remains unaffected.
CD is increased, while CL remains unaffected.
For a given aeroplane which two main variables determine the value of VMCG?
Airport elevation and temperature.
Engine thrust and rudder deflection.
Air density and runway length.
Engine thrust and gear position.
The total pressure: (note: rho = densiry)
can be measured in a small hole in a surface, parallel to the local stream.
is the static pressure plus the dynamic pressure.
is the static pressure minus the dynamic pressure.
is ½ rho V² .
Which part of the aeroplane has the largest effect on induced drag?
Wing root junction.
Engine cowling.
Wingtip
Landing gear.
A transonic Mach number is a Mach number:
between the buffet onset Mach number and the Mach number corresponding to total supersonic flow.
at which only supersonic local speeds occur.
in the range between MCRIT and MMO
which both subsonic and supersonic local speeds occur.
On an aircraft with an all -moving tail plane. backward movement of the control wheel in flight causes:
an increase in tail plane incidence and a nose up pitch.
an upward movement of the trimming tab and a nose up pitch.
an increase in tail plane incidence and a nose down pitch.
a decrease in tail plane incidence and a nose up pitch.
Which statement is correct about the gust load on an aeroplane (lAS and all other factors of importance remaining constant)? 1) When the mass decreases, the gust load factor increases. 2) When the altitude increases, the gust load factor increases.
1) is incorrect, 2) is correct.
1) is correct, 2) is correct.
1) is incorrect, 2) is incorrect
1) is correct, 2) is incorrect.
Which of these statements about flutter are correct or incorrect? 1) Aero-elastic coupling does not affect flutter characteristics. 2) The risk of flutter increases as lAS increases.
1) is correct, 2) is correct.
1) is incorrect, 2) is correct
1) is incorrect, 2) is incorrect
1) is correct, 2) is incorrect
The main purpose of a boundary-layer fence on a swept wing is to:
improve the lift coefficient of the trailing edge flaps.
improve the high speed handling characteristics.
improve the low speed handling characteristics.
increase the critical Mach number.
When the speed over an aerofoil section increases from subsonic to supersonic, its aerodynamic centre:
moves from approximately 25% to about 50% of the chord.
moves aft by approximately 10% of the chord.
does not move.
moves slightly forward.
Aileron flutter can be caused by:
aileron reversal.
cyclic deformations generated by aerodynamic, inertial and elastic loads on the wing.
continuous deformations in one direction generated by bending and twisting of the wing.
the elastic centre of the wing section coinciding with the centre of gravity of that wing section.
If density is kept constant, the dynamic pressure:
increases proportionally with velocity.
increases proportionally with static pressure.
changes inversely with the square of the velocity.
increases proportionally with the square of the velocity.
Which of these statements about "tuck under" are correct or incorrect? 1) A contributing factor to "tuck under" is an forward movement of the centre of pressure of the wing. 2) A contributing factor to "tuck under" is a reduction in the downwash angle at the location of the horizontal stabiliser.
1) is correct, 2) is correct.
1) is correct, 2) is incorrect.
1) is incorrect, 2) is correct.
1) is incorrect, 2) is incorrect.
From an initial condition of level flight the flaps are retracted at a constant pitch attitude. The aeroplane will subsequently:
start to sink.
start to climb.
start to bank.
maintain level flight.
A typical curve representing propeller efficiency of a fixed pitch propeller versus TAS at constant RPM is:
figure 4.
figure 2.
figure 1.
figure 3.
Compared to a straight wing of the same airfoil section a wing with a 30° sweep-back should theoretically have an MCRIT (i) times the MCRIT of the straight wing. However, in practice the swept wing will gain (ii) that increase.
i) 1.154, ii) half
i) 1.414, ii) twice
i) sine 30, ii) half
i) cosine 30, ii) twice
A swept wing compared to the same wing without sweep will provide:
the same lift at a given angle of attack and a lower CL MAX·
the same lift at a given angle of attack and a higher CL MAX·
less lift at a given angle of attack.
more lift at a given angle of attack.
The axes of an aircraft by definition must all pass through the:
flight desk.
aircraft datum.
centre of pressure.
centre of gravity.
The lift coefficient CL versus angle of attack curve of a negatively cambered aerofoil section intersects the horizontal axis of the graph:
to the right of the origin.
at the origin.
to the left of the origin.
nowhere
The lift coefficient (CL) of an aeroplane in steady horizontal flight is 0.42. An increase in angle of attack of 1 degree increases CL by 0.1. A vertical up gust instantly changes the angle of attack by 3°. The load factor will be:
1.71
1.49
2.49
0.74
A line conneaing the leading and trailing edge midway between the upper and lower surface of a aerofoil. This definition is applicable for:
the Mean Aerodynamic ChOrd line.
the chord line.
the camber line.
the upper camber line.
If the stall speed of an aeroplane is 60 kts, at what speed will the aeroplane stall if the load factor is 2?
120 kts.
66 kts.
72 kts.
85 kts.
Which is one of the disadvantages of excessive increasing of the number of propeller blades (beyond a certain number)?
Decreased propeller efficiency.
Increased noise.
Less power can be absorbed by the propeller.
Higher tip-speed.
The point in the diagram giving the lowest speed in unaccelerated horizontal flight is:
Point 3.
Point 4
Point 1
Point 2
Assuming no flow separation, which of these statements about the flow around an aerofoil as the angle of attack decreases are correct or incorrect? 1) The stagnation point moves down. 2) The point of lowest static pressure moves aft.
1) is correct, 2) is correct.
1) is correct, 2) is incorrect.
1) is incorrect, 2) is incorrect
1) is incorrect, 2) is correct.
An aeroplane is performing a co-ordinated level turn with a constant 30° bank angle. If the airspeed is increased the rate of turn will (i) and the radius ofturn will (ii).
i) increase; ii) decrease.
i) decrease; ii) increase.
i) increase; ii) increase.
i) decrease; ii) decrease.
The manoeuvrability of an aeroplane is best when the:
CG is on the aft CG limit.
speed is low.
CG position is on the forward CG limit.
flaps are down.
An increase in geometric dihedral in a steady sideslip condition at constant speed would:
decrease the required lateral control force.
increase the required lateral control force.
decrease the stick force per g.
not affect the required lateral control force.
The regime of flight from the critical Mach number up to approximately M = 1.3 is called the:
hypersonic range.
supersonic range.
transonic range.
subsonic range.
Which of these statements about a crimmable horizontal stabiliser is correct?
A trimmed aeroplane with an aft CG requires the stabiliser leading edge to be higher than in the case of a forward CG in the same condition.
A trimmed aeroplane with an aft CG requires the stabiliser leading edge to be lower than in the case of a forward CG in the same condition.
Because cake-off speeds do not vary with CG position, the need for stabiliser adjustment is dependent on flap position only.
At the aft CG limit, stabiliser trim is adjusted fully nose up to obtain maximum elevator authority at rotation during take-off.
As the centre of gravity is changed, recovery from a stall becomes progressively:
more difficult as the centre of gravity moves aft.
more difficult as the centre of gravity moves forward.
less difficult as the centre of gravity moves aft.
is unaffected by centre of gravity position. only by weight.
The point, where the aerodynamic lift acts on a wing is:
the CG location.
the centre of pressure.
the point of maximum thickness of the wing.
the suction point of the wing.
An aeroplane flying at 200 kts in straight and level flight is subjected to a disturbance that suddenly decreases the speed by 40 kt. Assuming the angle of attack remains constant, the load factor will initially:
decrease to 0.60.
decrease to 0.64.
decrease to 0.80.
remain unchanged, since the angle of attack does not change.
Which of these statements about the gust load factor on an aeroplane are correct or incorrect? 1) When the mass increases, the gust load factor increases. 2) When the altitude increases, the gust load factor increases.
1) is correct, 2) is incorrect.
1) is incorrect, 2) is correct.
1) is incorrect, 2) is incorrect.
1) is correct, 2) is correct.
When the blades of a propeller are in the feathered position:
the wind milling RPM is the maximum.
the propeller produces an optimal windmilling RPM.
the drag of the propeller is then minimal.
the RPM is then just sufficient to lubricate the engine.
In order to fly a rate one turn at a higher airspeed, the bank angle must be:
decreased and the turn radius will increase.
increased and the turn radius will decrease.
increased and the turn radius will increase.
decreased and the turn radius will decrease.
Which statement is correct regarding the gyroscopic effect of a clockwise rotating propeller on a single engine aeroplane? 1) Pitch up produces left yaw. 2) Right yaw produces pitch up.
1) is correct, 2) is correct.
1) is incorrect, 2) is incorrect
1) is correct, 2) is incorrect.
1) is incorrect, 2) is correct.
The application of the area rule on aeroplane design will decrease the:
wave drag.
skin friction drag.
induced drag.
form drag.
Assuming no compressibility effects, induced drag at constant lAS is affected by:
engine thrust.
aeroplane mass.
aeroplane wing location.
angle between wing chord and fuselage centre line.
What is the highest speed possible without supersonic flow over the wing?
Initial Mach buffet speed.
M = 1.
Tuck under speed.
Critical Mach number.
Increasing the number of propeller blades will:
decrease the torque in the propeller shaft at maximum power.
increase the propeller efficiency.
increase the noise level at maximum power.
increase the maximum absorption of power.
Assuming ISA conditions and a descent above the tropopause at constant Mach number and aeroplane mass, the:
lAS decreases.
TAS remains constant
lift coefficient increases.
lift coefficient remains constant.
Comparing the differences between a horizontal trimmable stabiliser and an elevator trim tab, which of these statements are correct or incorrect? 1) A stabiliser trim is more suitable to cope with the large trim changes generated by the high lift devices on most jet transport aeroplanes. 2) A stabiliser trim runaway causes less control difficulty.
1) is correct, 2) is incorrect.
1) is correct, 2) is correct.
1) is incorrect, 2) is incorrect
1) is incorrect, 2) is correct.
Considering subsonic incompressible airflow through a Venturi, which statement is correct? 1) The dynamic pressure in the undisturbed airflow is higher than in the throat. 2) The total pressure in the undisturbed airflow is higher than in the throat.
1) is correct. 2) is incorrect.
1) is incorrect, 2) is incorrect
1) is incorrect, 2) is correct.
1) is correct, 2) is correct.
What effect, if any, does altitude have on VMC for an aeroplane with unsupercharged engines?
Remains constant to full throttle height and then decreases.
Increases with increasing altitude.
Altitude has no effect.
Decreases with increasing altitude.
Which line in the diagram represents an aeroplane with static longitudinal instability at all angles of attack?
Line 2.
Line 4.
Line 3.
Line 1.
The function of the stick pusher is:
to activate and push the stick forward at or beyond a certain value of angle of attack.
to activate and push the stick forward prior to stick shaker.
to vibrate the controls.
to pull the stick, to avoid a high speed stall.
Which statement. about an aeroplane leaving ground effect at constant angle of attack, is correct? 1) The lift coefficient CL decreases. 2) The induced drag coefficient CDi remains constant.
1) is correct, 2) is incorrect.
1) is incorrect, 2) is correct.
1) is incorrect, 2) is incorrect
1) is correct, 2) is correct.
Mach buffet occurs:
direly after exceeding MCRIT·
when the Mach number has increased to MCRIT.
following boundary layer separation due to shock wave formation.
when the stall angle of attack is exceeded.
A jet aeroplane equipped with inboard and outboard ailerons as well as spoilers is cruising at its normal cruise Mach number. In this case:
outboard ailerons are locked out.
the inboard and outboard ailerons are active.
only the spoilers will be active, not the ailerons.
spoilers are locked out.
Considering subsonic incompressible airflow through a Venturi, which statement is correct? 1) The static pressure in the undisturbed airflow is the same as in the throat. 2) The speed in the undisturbed airflow is lower in the throat.
1) is correct. 2) Is incorrect.
1) is incorrect. 2) is correct.
1) is incorrect. 2) is incorrect
1) is correct. 2) is correct.
Which statement about a propeller is correct? 1) Asymmetric blade effect increases when engine power is increased. 2) Asymmetric blade effect reduces when the angle between the propeller axis and the airflow through the propeller disc increases.
1) is incorrect, 2) is correct
1) is incorrect, 2) is incorrect
1) is correct, 2) is incorrect
1) is correct, 2) is correct
Given: theta = pitch angle; gamma = flight path angle; alpha = angle of attack; no wind, bank or sideslip. The relationship between these three parameters is:
theta = gamma - alpha.
gamma = alpha - theta.
theta = gamma + alpha.
alpha = gamma - theta.
In straight flight, as speed is reduced, whilst trimming to keep the stick force zero:
the elevator is deflected further downwards and the trim tab further upwards.
the elevator is deflected further upwards and the trim tab further downwards.
both elevator and trim tab are deflected further upwards.
the elevator and trim tab do not move.
In a steady, horizontal, co-ordinated turn:
thrust equals drag, because there is equilibrium of forces along the direction of flight.
thrust is greater than drag, because the centrifugal force reduces the aeroplane speed.
thrust is greater than drag, because the excess thrust also supplies the centripetal force.
thrust equals drag, because drag is the same as in straight and level flight.
Which three aerodynamic means decrease manoeuvring stick forces?
Servo tab - horn balance - spring tab.
Servo tab - trim tab - balance tab.
Spring tab · trim tab - mass balancing weight
Spring tab - horn balance – bobweight
Regarding deep stall characteristics, identify whether the following statements are correct or incorrect: 1) The combination of a wing with sweepback and a T-tail make an aeroplane prone to deep stall. 2) A stick pusher system can be fined to an aeroplane that exhibits abnormal stall characteristics.
1) is correct, 2) is correct.
1) is correct, 2) is incorrect.
1) is incorrect, 2) is correct.
1) is incorrect, 2) is incorrect
Wing flutter can be prevented by:
ensuring that the wing CG is ahead of its torsional axis.
mounting the engines on the fuselage.
increasing wing elasticity.
increasing the aspect ratio of the wing.
The lift coefficient (CL) of an aeroplane in steady horizontal flight is 0.4. Increase of angle of attack of 1° will increase CL by 0.09. A vertical up-gust instantly changes the angle of attack by 5°. The load factor will be:
3.18
1.09
2.0
2.13
Which statement is correct? 1) A propeller with a small blade angle is referred to as being in fine pitch. 2) A propeller with significant blade twist is referred to as being in coarse pitch.
1) is correct, 2) is incorrect.
1) is incorrect, 2) is incorrect
1) is correct, 2) is correct.
1) is incorrect, 2) is correct.
Geometric washout (wing twist) means that
there is an airflow along the wing chat keeps It clean (prevents ice accumulation in flight).
the tip of the wing has higher angle of attack than the root.
the tip of the wing has lower angle of attack than the root.
the horizontal tail has lower angle of attack than the wing.
The interference drag is the result of:
separation of the induced vortex.
the addition of induced and parasite drag.
interaction between aeroplane parts (e.g. wing/fuselage).
downwash behind the wing.
The lift coefficient CL versus angle of attack curve of a symmetrical aerofoil section Intersects the horizontal axis of the graph:
at the origin.
to the right of the origin.
nowhere
to the left of the origin.
Regarding a symmetrical aerofoil section, which statement is correct? 1) The angle of attack has a negative value when the lift coefficient equals zero. 2) A nose up pitching moment exists when the lift coefficient equals zero.
1) is incorrect, 2) is correct.
1) is incorrect, 2) is incorrect.
1) is correct, 2) is incorrect.
1) is correct, 2) is correct.
The dynamic pressure is equal to: (note: p = density, v = speed)
p x V²
½p x V
½p x V²
½V x density²
The additional increase of drag at Mach numbers above the critical Mach number is due to:
increased angle of attack.
wave drag.
increased interference drag.
increased skin friction.
In a convergent tube with an incompressible sub-sonic airflow. the following pressure changes will occur: Ps = static pressure; PDYN = dynamic pressure; PTOT = total pressure
Ps decreases, PDYN increases. static temperature increases.
Ps increases. PDYN decreases. PTOT remains constant
Ps decreases, PDYN increases. PTOT remains constant
Ps decreases, PTOT increases, static temperature decreases
An accumulation of frost on an aircraft's wing will result in:
a decrease in lift and drag.
an increase in lift and a decrease in drag.
a decrease in lift and an increase in drag.
an increase in lift and drag.
An aeroplane's sideslip angle is defined as the angle between the:
lateral axis and the horizontal plane.
speed vector and the horizontal plane.
speed vector and normal axis.
speed vector and the plane of symmetry.
Regarding a positively cambered aerofoil section, which statement is correct? 1) The angle of attack has a negative value when the lift coefficient equals zero. 2) A nose down pitching moment exists when the lift coefficient equals zero.
1) is incorrect, 2) is correct.
1) is correct, 2) is incorrect.
1) is incorrect, 2) is incorrect
1) is correct, 2) is correct.
What kind of horizontal control surface is shown in the figure?
Canard
All-flying tail.
Elevator
Frise type control
The unit of measurement of pressure is:
kg/dm²
lb/gal
psi
kg/m³
Which statement about an aeroplane entering ground effect is correct? 1) The downwash angle remains constant. 2) The induced angle of attack increases.
1) is incorrect, 2) is correct
1) is correct, 2) is incorrect
1) is correct, 2) is correct
1) is incorrect, 2) is incorrect
Considering subsonic incompressible airflow through a Venturi, which statement is correct? 1) The static pressure in the throat is the same as in the undisturbed airflow. 2) The speed of the airflow in the throat is higher than in the undisturbed airflow.
1) is correct, 2) is incorrect.
1) is incorrect, 2) is incorrect
1) is correct, 2) is correct.
1) is incorrect, 2) is correct.
Given a constant load factor, which of these statements about the variation of induced drag with changes of speed and mass are correct or incorrect? 1) When speed decreases, induced drag decreases. 2) When mass decreases. induced drag decreases.
1) is correct, 2) is incorrect
1) is incorrect, 2) is correct
1) is incorrect, 2) is incorrect
1) is correct, 2) is correct
When flaps are extended whilst maintaining straight and level flight at constant lAS, the lift coefficient will:
eventually remain the same.
eventually increase.
eventually decrease.
first increase and then decrease.
Which of these statements about the gust load factor on an aeroplane are correct or incorrect? 1) When the slope of the lift versus angle of attack curve increases, the gust load factor increases. 2) When the wing loading increases, the gust load factor decreases.
1) is incorrect, 2) is incorrect
1) is correct, 2) is incorrect.
1) is incorrect, 2) is correct.
1) is correct, 2) is correct.
On an aircraft with a differential aileron control system, when the control wheel is turned to the right:
the right aileron moves up, and the left aileron moves down through a greater angle.
the right aileron moves down and the left aileron moves up through a greater angle.
the left aileron moves down and the right aileron moves up through a greater angle.
the left aileron moves up and the right aileron moves down through a greater angle.
Which statement is correct? 1) A propeller with a small blade angle is referred to as being in coarse pitch. 2) A propeller with a large blade angle is referred to as being in fine pitch.
1) is correct, 2) is correct.
1) is incorrect, 2) is correct.
1) is incorrect, 2) is incorrect.
1) is correct, 2) is incorrect.
The primary purpose of equipping the power assisted flying control systems with trim capability is to:
allow the pilot to maintain control in case of hydraulic failure.
relieve stresses on the trim tab.
relieve stresses on the hydraulic actuators.
bring the control forces to zero in steady flight.
