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WorksheetsM08 P2
Total questions: 92
Worksheet time: 46mins
'Load factor' has the following meaning:
The ratio of a specified load to the mass of the aircraft the former being expressed in terms of aerodynamic and inertia forces
The ratio of a specified load to the mass of the aircraft, the former being expressed in terms of aerodynamic forces, inertia forces and ground reactions
The ratio of a specified load to the weight of the aircraft, the former being expressed in terms of aerodynamic forces, inertia forces and ground reactions
Which of the following are lift increasing device?
Flaps only
Slots only
Flaps and slots
A boundary layer fence on a swept wing will
improve the high speed characteristics
increase the critical Mach Number
improve the low speed characteristics
A deployed slat will
increase the camber of the aerofoil and increase the effective angle of attack, suction peak so that Clmax is reached at higher angle of attack
increase the boundary layer energy and increase the suction peak on the fixed part of the wing, so that the stall is postponed to higher angle of attack
increase the boundary layer energy, move the suction peak from the fixed part of the wing to the slat, the stall is postponed to higher angle of attack
The type of flaps which increase both lift and area of the wing is a
slotted flap
plain flap
Fowler flap
What happens to lift when flaps are lowered?
Decreases
Remains same
Increases
In a gliding flight
lift is greater than weight
lift is less than weight
lift is zero
A slotted flap will increase the CLmax by
increasing only the camber of the aerofoil
increasing the camber of the aerofoil and improving the boundary layer
increasing the critical angle of attack
A stall warning device must be set to operate
at a speed just above stalling speed
at a speed just below stalling speed
at the stalling speed
A stick shaker is intended to come into operation
prior to the actual moment of aircraft stall
at the actual moment of aircraft stall
immediately after the aircraft is stalled
A wing flap is a
high lift device
primary control surface
secondary control surface
A wing stalling angle is
decreased in a turn
unaffected by a turn
increased in a turn
About which axis of the aircraft does a rolling motion take place?
Vertical axis
Longitudinal axis
Lateral axis
After take-off the slats (when installed) are always retracted later than the flaps. Why?
Because SLATS EXTENDED gives a large decrease in stall speed with relatively less drag
Because SLATS EXTENDED provides a better view from the cockpit than FLAPS EXTENDED
Because FLAPS EXTENDED gives a large increase in stall speed with relatively less drag
Aircraft flying in the transonic range most often utilize
high wings
sweptback wings
advanced super-critical airfoils
An aeroplane has the following flap settings: 0°, 15°, 30° and 45°. Slats can be selected too. Which of the above selections will produce the greatest negative influence on the CL/CD ratio?
Flaps from 15° to 30°
Flaps from 30° to 45°
Flaps from 0° to 15°
An aircraft banks into a turn. No change is made to the airspeed or angle of attack. What will happen?
The aircraft enters a side slip and begins to lose altitude
The aircraft turns with no loss of height
The aircraft yaws and slows down
An aircraft entering a level turn will require more lift
in all cases
only if there is an increase in speed
only if there is an increase in angle of attack
An aircraft is flying into the wind. In a given amount of time, it will
fly with the same IAS as in still air, but travel less distance
fly with a higher IAS than in still air, and travel further
fly with a higher IAS than in still air, and travel less
An aircraft wing is said to have stalled when the
boundary layer is completely turbulent
speed of the aircraft falls below the stalling speed
airflow separates from the upper surface
An increase in angle of attack (below the stalling angle of attack) increases lift because
induced drag is reduced
the vertical component of weight is reduced
the lift coefficient increases
An increase of wing loading will
increase the stall speed
decrease the minimum gliding angle
decrease take off speeds
Balancing of the weight component along the flight path in a glide is achieved by
drag
lift
thrust and drag
CLmax may be increased by the use of
flaps
slats
both flaps and slats
Compared with stalling airspeed (VS) in a given configuration, the airspeed at which stick shaker will be triggered is
VS
greater than VS
less than VS
Compared with the flap down configuration the maximum angle of attack for the flaps up configuration is
larger
unchanged
smaller
Compared with the flap up configuration the maximum angle of attack for the flaps down configuration is
larger
smaller
unchanged
Deploying a Fowler flap, the flap will
turn down, then move aft
move aft, then turn down
just move aft
Deployment of leading edge flaps will
decrease CLmax
increase critical angle of attack
decrease drag
Directional control is provided by
rudder
horizontal stabilizer
elevator
During flap down selection in a continuous straight and level flight at constant IAS and weight
the stall speed increases
the lift coefficient and the drag coefficient increase
the centre of pressure moves aft
During the extension of the flaps at a constant angle of attack the aeroplane starts to: (all other factors of importance being constant)
sink suddenly.
climb
bank
Entering the stall the centre of pressure of a straight wing (1) and of a strongly swept back wing (2) will
(1) move aft, (2) move forward
(1) not move (2) move forward
(1) move aft, (2) not move
Flaps are said to be split when
left and right flaps operate independently
the upper surface of the wing trailing edge is fixed, and only the lower surface contour alters when the flaps are lowered
flaps are manufactured in several sections to allow for wing flexing
For the same angle of attack, the lift on a delta wing
is lower than the lift on a high aspect ratio wing
is the same as the lift on a high aspect ratio wing
is greater than the lift on a high aspect ratio wing
High Aspect Ratio, as compared with low Aspect Ratio, has the effect of
increasing induced drag and decreasing critical angle of attack
increasing lift and critical angle of attack
decreasing induced drag and critical angle of attack
How is the pitching moment affected if flaps are deployed in straight and level flight?
Pitch down
Depends on wing position
Pitch up
If a plain flap is lowered or extended
angle of attack increases
both camber and angle of attack increase
camber increases
In a bank and turn
extra lift is not required
extra lift is required
extra lift is not required if thrust is increased
In a bank, the weight is
decreased
increased
the same
Low speed pitch-up is caused by the
span wise flow on a swept back wing
Mach trim system
wing tip vortex
Movement of an aircraft about its lateral axis
is pitching
is yawing
is rolling
On a very humid day, an aircraft taking off would require
a shorter take off run
humidity does not affect the take off run
a longer take off run
One of the main purposes of using flaps during approach and landing is to
increase the angle of descent without increasing the airspeed
shift the centre of gravity aft
decrease the angle of descent without increasing the airspeed
Pulling the control column and rotating to the left causes
elevator down, left aileron down
elevator down, left aileron up
elevator up, left aileron up
he left causes
elevator down, left aileron down
elevator down, left aileron up
elevator up, left aileron up
Slats
reduce the tendency of the aircraft to Yaw
reduce the stall speed
decrease the aerofoil drag at high speeds
Slats
re-energise the boundary layer thereby increasing the stalling angle of attack
re-energise the boundary layer thereby decreasing the stalling angle of attack
de-energise the boundary layer, thereby decreasing the stalling angle of attack
Slats are used to
change the wing camber
ensure the boundary layer does not separate from the wing surface too soon
decrease the stalling angle
Stall strips are always
fitted forward of the ailerons
made of metal
on the leading edge of a wing
Stick pusher is installed in aircraft when
the aircraft has failed to meet the stalling requirements by normal category
the aircraft has no yaw damper installed
the aircraft is directional unstable
Stick pushers must be installed in aeroplanes with dangerous stall characteristics. Dangerous stall characteristics include:
pitch down and increase in speed
excessive wing drop and deep stall
pitch down and minor wing drop
The aerodynamic load factor
is unaffected by turns
is constant if the wing area is constant
increases if the radius of turn decreases
The angle of attack at which a wing stalls will
remain the same regardless of centre of gravity position
increase if the centre of gravity is moved aft
increase if the centre of gravity is moved forward
The critical angle of attack
changes with an increase in gross weight
increases if the CG is moved forward
remains unchanged regardless of gross weight
The difference between IAS and TAS is
TAS increases with increasing density
TAS decreases with decreasing altitude
TAS increases with decreasing temperature
The force opposing thrust is
lift
Weight
Drag
The function of the slot between an extended slat and the leading edge of the wing is to
cause venturi effect which energizes the boundary layer
reduce the wing loading
slow the air flow in the slot so that more pressure is created under the wing
The L/D ratio in flight will be at its highest value at
a point just below the stalling angle
the stalling angle
the optimum angle of attack
The preferred arrangement of forces on an aircraft are such that
lift is in front of weight
weight is in front of thrust
weight is in front of lift
The power required in a horizontal turn
must be the same as that for level flight at the same airspeed
is less than that for level flight at the same airspeed
is greater than that for level flight at the same airspeed
The lateral axis is
a straight line through the CG parallel to a line joining the wingtips
a straight line through the CG from nose to tail
a straight line through the CG at right angles to the longitudinal and lateral axis
The lateral axis is also called the
pitch axis
normal axis
roll axis
Dihedral wings combat instability in
side-slip
pitch
yaw
An aircraft with neutral stability has its attitude changed due to a gust of wind, how will this effect it?
It will return to its original attitude
It will go further out of control continuously
It will remain in its new attitude
The directional axis
acts through the C of G, perpendicular to the longitudinal axis and lateral axis
is perpendicular to the longitudinal axis
is perpendicular to the horizontal axis
If an aircraft returns to a position of equilibrium it is said to be
positively stable
neutrally stable
negatively stable
Which of the following is used to counteract yaw?
Fin area
Lateral dihedral
Longitudinal dihedral
Dutch roll is an oscillatory motion that is an interaction between
longitudinal and directional stability
lateral and directional stability
longitudinal and lateral stability
Lateral stability is about the
vertical axis
longitudinal axis
lateral axis
Dutch Roll is
a type of slow roll
primarily a pitching instability
a combined rolling and yawing motion
Movement of an aircraft about its vertical axis
is yawing
is pitching
is rolling
The pendulum effect on a high wing aircraft
increases lateral stability
decreases lateral stability
has no effect on lateral stability
As the centre of gravity is changed, recovery from a stall
becomes progressively more difficult as the centre of gravity moves aft.
becomes progressively more difficult as the centre of gravity moves forward
is unaffected by centre of gravity position
Longitudinal stability is provided by the
horizontal stabilizer
vertical stabilizer
mainplane
The fin gives stability about which axis?
Lateral axis
Vertical axis
Longitudinal axis
Dihedral improves
longitudinal stability
directional stability
lateral stability
An aircraft, which is longitudinally stable, will tend to return to level flight after a movement in which axis?
Roll
Yaw
Pitch
If the nose of the aircraft is rotated about its lateral axis, what is its directional movement?
Climbing or diving
Turning to the left or right
Rolling or banking to the left or right
Stability of an aircraft is
the ability of the aircraft to rotate about an axis
the tendency of the aircraft to stall at low airspeed
the tendency of the aircraft to return to its original trimmed position after having been displaced
A high wing position gives
the same lateral stability as a low wing
more lateral stability than a low wing
less lateral stability than a low wing
The three axes concerned with stability of an aircraft have
longitudinal axis nose to tail, lateral axis at furthest span point, vertical axis through centre of pressure
vertical axis through C of G. Lateral axis - wing tip to wing tip. Longitudinal axis - nose to tail but not through C of G
longitudinal, lateral and vertical axis all passing through aircraft centre of gravity
Yawing is a rotation around
the vertical axis obtained by the elevator
the lateral axis obtained by the rudder
the vertical axis obtained by the rudder
Lateral stability may be increased with
increased longitudinal dihedral
increased lateral anhedral
increased lateral dihedral
What gives the aircraft directional stability?
Vertical stabiliser
Horizontal stabiliser
Elevators
Where would you find the vertical axis?
Through C of G at right angles to longitudinal and lateral axis
In line with the wing tips through C of G
Vertically through C of P
The reduction in oscillation after certain disturbances to the aircraft is known as
neutral dynamic stability
static stability
dynamic stability
Some aeroplanes are built with lateral dihedral. The purpose of this is to contribute to
lateral stability
longitudinal stability
directional stability
The static stability of an aircraft is its
ability to return to its original trim position
balance around its CofG
manoeuvrability
What is longitudinal stability?
Stability of aircraft about its vertical axis
Stability of aircraft about its longitudinal axis
Stability of aircraft about its lateral axis
The vertical axis of an aircraft passes through
a point at the centre of the wings
the centre of gravity
the centre of pressure
An aircraft disturbed from its normal flight path, and automatically returns to that normal flight path, without any action on the part of the pilot is known as
aircraft instability
aircraft stall
aircraft stability
