EASA Module 8 : Basic Aerodynamics Questions
EASA Module 8 : Basic Aerodynamics Question-Answer
An increase in the speed at which an aerofoil passes through the air increases lift because
Ans a) the increased speed of the airflow creates a greater pressure differential between the upper and lower surfaces.
b) the increased speed of the airflow creates a lesser pressure differential between the upper and lower surfaces.
c) the increased velocity of the relative wind increases the angle of attack
A delta wing has
Ans a) a higher stall angle than a straight wing b) a lower stall angle than a straight wing c) the same stall angle than a straight wing
The Lift/Drag ratio of a wing at the stalling angle is
a) of a negative value Ans b) low c) high
The airflow over the upper surface of a cambered wing
a) increases in velocity and pressure Ans b) increases in velocity and reduces in pressure
c) reduces in velocity and increases in pressure
The speed of air over a swept wing which contributes to the lift is
a) less than the aircraft speed Ans b) more than the aircraft speed c) the same as the aircraft speed
For a given angle of attack induced drag is
a) greater on a high aspect ratio wing b) greater towards the wing root Ans c) greater on a low aspect ratio wing
In straight and level flight, the angle of attack of a swept wing is
a) the same as the aircraft angle to the horizontal Ans b) more than the aircraft angle to the horizontal
c) less than the aircraft angle to the horizontal
Induced drag
a) is never equal to the profile drag b) is equal to the profile drag at the stalling speed Ans c) is equal to the profile drag at Vmd
A delta wing aircraft flying at the same speed (subsonic) and angle of attack as a swept wing aircraft of similar wing area will produce
a) the same lift b) more lift Ans c) less lift
The stagnation point is
Ans a) static pressure plus dynamic pressure b) static pressure minus dynamic pressure c) dynamic pressure only
On a swept wing aircraft, due to the adverse pressure gradient, the boundary layer on the upper surface of the wing tends to flow
a) directly from leading edge to trailing edge Ans b) towards the tip c) towards the root
With increased speed in level flight
a) induced drag increases Ans b) profile drag increases c) profile drag remains constant
If a swept wing stalls at the tips first, the aircraft will
Ans a) pitch nose up b) pitch nose down c) roll
The thickness/chord ratio of the wing is also known as
a) aspect ratio b) mean chord ratio Ans c) fineness ratio
Flexure of a rearward swept wing will
a) increase the lift and hence increase the flexure Ans b) decrease the lift and hence decrease the flexure
c) increase the lift and hence decrease the flexure
A High Aspect Ratio wing is a wing with
a) long span, long chord Ans b) long span, short chord c) short span, long chord
Stall commencing at the root is preferred because
a) the ailerons become ineffective Ans b) it provides the pilot with a warning of complete loss of lift
c) it will cause the aircraft to pitch nose up
An aircraft flying in “ground effect” will produce
Ans a) more lift than a similar aircraft outside of ground effect
b) less lift than a similar aircraft outside of ground effect
c) the same lift as a similar aircraft outside of ground effect
If the angle of attack of a wing is increased in flight, the
Ans a) C of P will move forward b) C of G will move aft c) C of P will move aft
The Rams Horn Vortex on a forward swept wing will be
a) the same as a rearward swept wing b) more than a rearward swept wing Ans c less than a rearward swept wing
When maintaining level flight an increase in speed will
a) cause the C of P to move aft b) cause the C of P to move forward Ans c) have no affect on the position of the C of P
For a cambered wing section the zero lift angle of attack will be
a) zero b) 4 degrees Ans c) negative
Density changes with altitude at a rate
a) of 2kg/m3 per 1000ft Ans b) which changes with altitude c) which is constant until 11km
Airflow at subsonic speed is taken to be
a) compressible Ans b) incompressible c) either a or b depending on altitude
Bernoulli's equation shows that
Ans a) at constant velocity the kinetic energy of the air changes with a change of height
b) with a change in speed at constant height both kinetic and potential energies change
c) with a change in velocity at constant height the static pressure will change
If fluid flow through a venturi is said to be incompressible, the speed of the flow increases at the throat to
Ans a) maintain a constant volume flow rate b) allow for a reduction in static pressure c) allow for an increase in static pressure
To produce lift, an aerofoil must be
a) asymmetrical b) symmetrical Ans c) either a or b above
Lift is dependent on
Ans a) the area of the wing, the density of the fluid medium, and the square of the velocity
b) the net area of the wing ,the density of the fluid medium and the velocity
c) the frontal area of the wing, the density of the fluid medium and the velocity
The maximum lift/drag ratio of a wing occurs
a) at the angle of attack where the wing develops its maximum lift
b) during take off Ans c) at an angle below which the wing develops max lift
A wing develops 10,000N of lift at 100knots. Assuming the wing remains at the same angle of attack and remains at the same altitude, how much lift will it develop at 300knots?
a) 900,000 N Ans b) 90,000N c) 30,000N
The angle of attack is
a) related to angle of incidence b) always kept below 15 degrees Ans c) not related to the angle of incidence
The difference between the mean camber line and the chord line of an aero foil is
Ans a) one is always straight and the other may be straight b) neither are straight c) they both may be curved
If the C of G is calculated after loading as within limits for take off
a) no further calculation is required
Ans b) a further calculation is required prior to landing to allow for fuel and oil consumption
c) a further calculation is required prior to landing to allow for flap deployment
A stalled aero foil has a lift/drag ratio
a) more than the lift/drag ratio prior to stall b) Zero Ans c) Less than the lift/drag ratio prior to stall
At low forward speed
a) Increased downwash reduces tail plane effectiveness
Ans b) increased downwash increases tail plane effectiveness
c) Excessive rudder movement may cause fin to stall
Helicopter rotor blades create lift by
Ans a) creating low pressure above the blades
b) Pushing the air down c) Working like a screw
On some modern aircraft a stall warning will automatically
a) Increase thrust b) Extend outboard slats
Ans c) cause a pitch nose down movement
Upward and outward inclination of a mainplane is termed
a) sweep Ans b) dihedral c) stagger
The function of an aircraft fin
Ans a) is to provide stability about the normal axis
b) is to provide directional control
c) is to provide straight airflow across the rudder
Movement of an aircraft about its normal axis
a) is pitching b) is rolling Ans c) is yawing
A pressure of one atmosphere is equal to
Ans a) 14.7 psi b) 100 millibar c) 1 inch Hg.
The millibar is a unit of
a) atmospheric temperature b) pressure altitude Ans c) barometric pressure
With an increase in altitude under I.S.A. conditions the temperature in the troposphere
a) increases Ans b) decreases c) remains constant
Which of the following forces act on an aircraft in level flight?
a) Lift, thrust, and weight Ans b) Lift, thrust, weight, and drag c) Lift, drag, thrust
When an aircraft is banked, the horizontal component of the lift
Ans a) will tend to make the aircraft follow a circular path
b) will oppose the tendency of the aircraft to follow a circular path
c) will oppose the weight thus requiring more total lift in the turn
If, after a disturbance, an aeroplane initially returns to its equilibrium state
a) it has neutral stability Ans b) it has static stability and may be dynamically stable c) it is neutrally unstable
Stability of an aircraft is
Ans a) the tendency of the aircraft to return to its original trimmed position after having been displaced
b) the ability of the aircraft to rotate about an axis
c) the tendency of the aircraft to stall at low airspeeds
With reference to altimeters QFE is
Ans a) setting aerodrome atmospheric pressure so that an altimeter reads zero on landing and take off
b) quite fine equipment c) the manufacturers registered name
Under the ICAO “Q” code there are which three settings?
Ans a) QFE , QNH , QNE b)QEF , QNH , QEN c) QE , QN , QQE
Wing loading is
Ans a) GROSS WEIGHT divided by GROSS WING AREA
b) WING AREA x WING CHORD
c) the ultimate tensile strength of the wing
The three axes concerned with stability of an aircraft have
a) normal axis through C of G. Lateral axis - wing tip to wing tip. Longitudinal axis - nose to tail but not through C of G
Ans b) longitudinal, lateral and normal axis all passing through aircraft centre of gravity
c) longitudinal axis nose to tail, lateral axis at furthest span point, normal axis through centre of pressure
A barometer indicates
Ans a) pressure b) density c) temperature
If an aircraft returns to a position of equilibrium it is said to be
a) negatively stable b) neutrally stable Ans c) positively stable
The pendulum effect on a high wing aircraft
Ans a) increases lateral stability b) decreases lateral stability c) has no effect on lateral stability
The amount of water vapour in the air (humidity holding capacity of the air) is
a) greater on a colder day, and lower on a hotter day Ans b) greater on a hotter day and lower on a colder day
c) doesn't have a significant difference
Weight is equal to
a) volume x gravity b) mass x acceleration Ans c) mass x gravity
Induced Drag
a) increases with an increase in speed b) reduces with an increase in angle of attack
Ans c) increases with increase in aircraft weight
Airflow over the upper surface of the wing generally
Ans a) flows towards the root b) flows towards the tip c) flows straight from leading edge to trailing edge
with an increase in aspect ratio for a given ISA, induced drag will
a) remain constant b) increase Ans c) reduce
With increasing altitude the angle at which a wing will stall
Ans a) remains the same b) reduces c) increases
If the density of the air is increased, the lift will
Ans a) increase b) decrease c) remain the same
All the factors that affect the lift produced by an aerofoil are
a) angle of attack, air density, velocity, wing area
b) angle of attack, air temperature, velocity, wing area
Ans c) angle of attack, velocity, wing area, aerofoil shape, air density
A wing section suitable for high speed would be
a) thick with high camber b) thin with high camber Ans c) thin with little or no camber
The induced drag of an aircraft
a) increases with increasing speed b) increases if aspect ratio is increased Ans c) decreases with increasing speed
As the speed of an aircraft increases the profile drag
Ans a) increases b) decreases c) decreases at first then increase
The stagnation point on an aerofoil is the point where
a) the suction pressure reaches a maximum
b) the boundary layer changes from laminar to turbulent
Ans c) the airflow is brought completely to rest
After a disturbance in pitch, an aircraft continues to oscillate at constant amplitude. It is
a) longitudinally unstable Ans b) longitudinally neutrally stable c) laterally unstable
On an aircraft with an all-moving tailplane nose up pitch is caused by
a) increasing tailplane incidence Ans b) decreasing tailplane incidence c) up movement of the trim tab
The stalling of an aerofoil is affected by the
a) airspeed Ans b) angle of attack c) transition speed
What gives the aircraft directional stability?
Ans a) Vertical stabiliser b) Horizontal stabiliser c) Elevators
The most fuel efficient of the following types of engine is the
a) rocket b) turbo-jet engine Ans c) turbo-fan engine
The quietest of the following types of engine is the
a) rocket b) turbo-jet engine Ans c) turbo-fan engine
Forward motion of a glider is provided by
a) the engine Ans b) the weight c) the drag
Profile drag consists of what drag types?
Ans a) Form, skin friction and interference b) Form, induced and skin friction c) Form, induced and interference
An aircraft in straight and level flight is subject to
a) zero load factor Ans b) a load factor of 1 c) a load factor of ½
Aspect ratio is given by the formula
a) Mean Chord Span Ans b) Span2 Area c) Span2 Mean Chord
On a high wing aircraft in a turn
a) the up going wing loses lift which has a de-stabilizing effect
Ans b) the down going wing gains lift causing a stabilizing effect
c) the down going wing loses lift causing a de-stabilizing effect
Which condition is the actual amount of water vapour in a mixture of air and water?
a) Relative humidity b) Dew point Ans c) Absolute humidity
An aspect ratio of 8 means
Ans a) the span is 8 times the mean chord b) the mean chord is 8 times the span c) the area is 8 times the span
The ISA
a) is taken from the equator b) is taken from 45 degrees latitude Ans c) assumes a standard day
Which will weigh the least?
Ans a) 98 parts of dry air and 2 parts of water vapour b) 35 parts of dry air and 65 parts of water vapour
c) 50 parts of dry air and 50 parts of water vapour
A high aspect ratio wing
a) is stiffer than a low aspect ratio wing Ans b) has less induced drag than a low aspect ratio wing
c) has a higher stall angle than a low aspect ratio wing
The thrust-drag couple overcomes the lift-weight couple. What force must the tail of the aircraft exert to maintain the aircraft in a level attitude?
a) Down Ans b) Up c) Sideways
Induced downwash
Ans a) reduces the effective angle of attack of the wing
b) increases the effective angle of attack of the wing
c) has no effect on the angle of attack of the wing
during a turn, the stalling angle
a) increases b) decreases Ans c) remains the same
Which is the ratio of the water vapour actually present in the atmosphere to the amount that would be present if the air were saturated at the prevailing temperature and pressure?
a) Absolute humidity Ans b) Relative humidity. c) Dew point
A straight rectangular wing, without any twist, will
a) have greater angle of attack at the tip
b) have the same angle of attack at all points along the span
Ans c) have less angle of attack at the tip
If gauge pressure on a standard day is 25 PSI, the absolute pressure is
a) 10.3 PSI b) 43.8 PSI Ans c) 39.7 PSI
The C of G moves in flight. The most likely cause of this is
a) movement of passengers b) movement of cargo Ans c) consumption of fuel and oils
The speed of sound in the atmosphere
a) varies according to the frequency of the sound
Ans b) changes with a change in temperature c) changes with a change in pressure
A straight rectangular wing, without any twist, will
a) stall first at the tip Ans b) stall first at the root
c) stall equally along the span of the wing
What is sea level pressure?
Ans a) 1013.2 mb b) 1012.3 mb c) 1032.2 mb
Which atmospheric conditions will cause the true landing speed of an aircraft to be the greatest?
a) Low temperature with low humidity b) High temperature with low humidity Ans c) High temperature with high humidity
Which condition is the actual amount of water vapour in a mixture of air and water?
a) Relative humidity b) Dew point Ans c) Absolute humidity
When the weight of an aircraft increases, the minimum drag speed
a) decreases Ans b) increases c) remains the same
Which statement concerning heat and/or temperature is true?
a) There is an inverse relationship between temperature and heat.
Ans b) Temperature is a measure of the kinetic energy of the molecules of any substance
c) Temperature is a measure of the potential energy of the molecules of any substance
Which is the ratio of the water vapour actually present in the atmosphere to the amount that would be present if the air were saturated at the prevailing temperature and pressure?
a) Absolute humidity Ans b) Relative humidity c) Dew point
When an aircraft experiences induced drag
Ans a) air flows under the wing spanwise towards the tip and on top of the wing spanwise towards the root
b) air flows under the wing spanwise towards the root and on top of the wing spanwise towards the tip
c) Neither a) or b) since induced drag does not cause spanwise flow
What is absolute humidity?
a) The temperature to which humid air must be cooled at constant pressure to become saturated.
Ans b) The actual amount of the water vapour in a mixture of air and water
c) The ratio of the water vapour actually present in the atmosphere to the amount that would be present if the air were saturated at the prevailing temperature and pressure
Which atmospheric conditions will cause the true landing speed of an aircraft to be the greatest?
a) Low temperature with low humidity b) High temperature with low humidity Ans c) High temperature with high humidity
If all, or a significant part of a stall strip is missing on an aeroplane wing, a likely result will be
a) increased lift in the area of installation on the opposite wing at high angles of attack
b) asymmetrical aileron control at low angles of attack
Ans c) asymmetrical aileron control at or near stall angles of attack
When a leading edge slat opens, there is a gap between the slat and the wing. This is
a) to allow it to retract back into the wing
Ans b) to allow air through to re-energize the boundary layer on top of the wing
c) to keep the area of the wing the same
An aeroplane wing is designed to produce lift resulting from relatively
a) positive air pressure below and above the wing's surface.
b) negative air pressure below the wing's surface and positive air pressure above the wing's surface.
Ans c) positive air pressure below the wing's surface and negative air pressure above the wing's surface
Aspect ratio of a wing is defined as the ratio of the
a) wingspan to the wing root b) square of the chord to the wingspan Ans c) wingspan to the mean chord
Which of the following is true?
a) Lift acts at right angles to the wing chord line and weight acts vertically down
Ans b) Lift acts at right angles to the relative airflow and weight acts vertically down
c) Lift acts at right angles to the relative air flow and weight acts at right angles to the aircraft centre line
The temperature to which humid air must be cooled at constant pressure to become saturated is called
Ans a) dewpoint b) absolute humidity c) relative humidity
The airflow over the upper surface of a cambered wing
a) increases in velocity and pressure Ans b) increases in velocity and reduces in pressure
c) reduces in velocity and increases in pressure
Which type of flap increases the area of the wing?
a) Plain Flap Ans b) Fowler Flap c) All flaps
If all, or a significant part of a stall strip is missing on an aeroplane wing, a likely result will be
a) increased lift in the area of installation on the opposite wing at high angles of attack
b) asymmetrical aileron control at low angles of attack Ans c) asymmetrical aileron control at or near stall angles of attack
With increased speed in level flight
a) induced drag increases Ans b) profile drag increases c) profile drag remains constant
Deployment of flaps will result in
Ans a) a decrease in stall angle b) an increase in stall angle c) a decrease in angle of attack
An aeroplane wing is designed to produce lift resulting from relatively
a) positive air pressure below and above the wing's surface.
b) negative air pressure below the wing's surface and positive air pressure above the wing's surface.
Ans c) positive air pressure below the wing's surface and negative air pressure above the wing's surface.
The angle of attack of an aerofoil section is the angle between the
Ans a) chord line and the relative airflow
b) underside of the wing surface and the mean airflow
c) chord line and the centre line of the fuselage
A swept wing tends to stall first at the
a) root Ans b) tip c) centre section
Kreuger Flaps are normally fitted to
a) the trailing edge of the wings b) the tips of the wings Ans c) the leading edge of the wings
Aspect ratio of a wing is defined as the ratio of the
a) wingspan to the wing root. b) square of the chord to the wingspan. Ans c) wingspan to the mean chord
The trailing vortex on a pointed wing (taper ratio = 0) is
a) at the root b) at the tip Ans c) equally all along the wing span
A high wing aircraft will be more
Ans a) laterally stable than a low wing aircraft b) longitudinally stable than a low wing aircraft
c) directionally stable than a low wing aircraft
A wing with a very high aspect ratio (in comparison with a low aspect ratio wing) will have
a) increased drag at high angles of attack. Ans b) a low stall speed. c) poor control qualities at low airspeeds.
The lift curve for a delta wing is
a) more steep than that of a high aspect ratio wing
Ans b) less steep than that of a high aspect ratio wing
c) the same as that of a high aspect ratio wing
after an aircraft has been disturbed from its straight and level flight, it returns to its original attitude with a small amount of decreasing oscillation. The aircraft is
a) statically stable but dynamically unstable
b) statically unstable but dynamically stable
Ans c) statically stable and dynamically stable
The angle of attack which gives the best L/D ratio
a) decreases with a decrease in density
Ans b) in unaffected by density changes
c) increases with a decrease in density
For a given aerofoil production lift, where
P = pressure and V = velocity:
a) P1 is greater than P2, and V1 is greater than V2
b) P1 is less than P2 and V1 is greater than V2
Ans c) P1 is greater than P2, and V1 is less than V2
Low wing loading
a) increases stalling speed, landing speed and landing run
b) increases lift, stalling speed and maneuverability
Ans c) decreases stalling speed, landing speed and landing run
Due to the change in downwash on an untapered wing (i.e. one of constant chord length) it will
a) not provide any damping effect when rolling
Ans b) tend to stall first at the root
c) not suffer adverse yaw effects when turning
True stalling speed of an aircraft increases with altitude
a) because reduced temperature causes compressibility effect
Ans b) because air density is reduced
c) because humidity is increased and this increases drag
As a general rule, if the aerodynamic angle of incidence (angle of attack) of an aerofoil is slightly increased, the centre of pressure will
a) never move Ans b) move forward towards the leading edge c) move towards the tip
The "wing setting angle" is commonly known as
Ans a) angle of incidence b) angle of attack c) angle of dihedral
On a very humid day, an aircraft taking off would require
a) a shorter take off run Ans b) a longer take off run c) humidity does not affect the takeoff run
An aircraft is flying at 350 MPH, into a head wind of 75 MPH, what will its ground speed be?
a) 175 mph Ans b) 275 mph c) 200 mph
When does the angle of incidence change?
a) When the aircraft attitude changes
b) When the aircraft is ascending or descending
Ans c) It never changes
As the angle of attack decreases, what happens to the centre of pressure?
a) It moves forward Ans b) It moves rearwards
c) Centre of pressure is not affected by angle of attack decrease
A decrease in pressure over the upper surface of a wing or aerofoil is responsible for
Ans a) approximately 2/3 (two thirds) of the lift obtained
b) approximately 1/3 (one third) of the lift obtained
c) approximately 1/2 (one half) of the lift obtained
Which of the four forces act on an aircraft?
Ans a) Lift, gravity, thrust and drag
b) Weight, gravity, thrust and drag
c) Lift, weight, gravity and drag
Which of the following types of drag increases as the aircraft gains altitude?
a) Parasite drag Ans b) Induced drag c) Interference drag
Correcting for a disturbance which has caused a rolling motion about the longitudinal axis would re-establish which of the following?
Ans a) Lateral stability b) Directional stability c) Longitudinal stability
The layer of air over the surface of an aerofoil which is slower moving, in relation to the rest of the airflow, is known as
a) camber layer Ans b) boundary layer c) none of the above
What is a controlling factor of turbulence and skin friction?
a) Aspect ratio b) Fineness ratio Ans c) Counter sunk rivets used on skin exterior
Changes in aircraft weight
a) will not affect total drag since it is dependant only upon speed
Ans b) cause corresponding changes in total drag due to the associated lift change
c) will only affect total drag if the lift is kept constant
The aircraft stalling speed will
Ans a) increase with an increase in weight
b) be unaffected by aircraft weight changes since it is dependant upon the angle of attack
c) only change if the MTMA were changed
In a bank and turn
a) extra lift is not required b) extra lift is not required if thrust is increased Ans c) extra lift is required
To maintain straight and level flight on the aeroplane shown, with a decrease in tail-plane download the mainplane lift would have to
a) remain constant Ans b) decrease c) increase
To achieve the maximum distance in a glide, the recommended air speed is
a) as close to the stall as practical b) as high as possible with VNE Ans c) the speed where the L/D ratio is maximum
If the C of G is aft of the Centre of Pressure
Ans a) changes in lift produce a pitching moment which acts to increase the change in lift
b) when the aircraft sideslips, the C of G causes the nose to turn into the sideslip thus applying a restoring moment
c) when the aircraft yaws the aerodynamic forces acting forward of the Centre of Pressure
Porpoising is an oscillatory motion in the
Ans a) pitch plane b) roll plane c) yaw plane
Directional stability is maintained
a) by the mainplanes, and controlled by the ailerons
b) by the tailplane, and controlled by the elevators
Ans c) by the keel surface and fin, and controlled by the rudder
Due to the interference effects of the fuselage, when a high wing aeroplane sideslips
a) the accompanying rolling due to keel surface area is destabilizing
Ans b) the accompanying lift changes on the wings produces a stabilizing effect
c) the accompanying rolling due to the fin is destabilizing
The power required in a horizontal turn
Ans a) is greater than that for level flight at the same airspeed
b) must be the same as that for level flight at the same airspeed
c) is less than that for level flight at the same airspeed
A wing mounted stall sensing device is located
Ans a) usually on the under surface b) always at the wing tip c) always on the top surface
For an aircraft in a glide
a) thrust, drag, lift and weight act on the aircraft
Ans b) weight, lift and drag act on the aircraft
c) weight and drag only act on the aircraft
The upper part of the wing in comparison to the lower
Ans a) develops more lift b) develops the same lift c) develops less lift
What effect would a forward CG have on an aircraft on landing?
Ans a) Increase stalling speed b) No effect on landing c) Reduce stalling speed
QNH refers to
a) Quite near horizon b) setting the altimeter to zero
Ans c) setting the mean sea level atmospheric pressure so an altimeter reads the aerodrome altitude above mean sea level
QNE refers to
Ans a) Setting an altimeter to read aerodrome altitude above sea level b) Quite new equipment
c) setting the mean sea level atmospheric pressure in accordance with ICAO standard atmosphere i.e. 1013 millibars
An aspect ratio of 8 would mean
Ans a) span 64, mean chord 8 b) mean chord 64 , span 8 c) span squared 64 ,chord 8
If an aircraft in level flight loses engine power it will
a) pitch nose up Ans b) pitch nose down c) not change pitch without drag increasing
QFE is
a) sea level pressure Ans b) airfield pressure c) difference between sea level and airfield pressure
The lift /drag ratio at stall
a) increases Ans b) decreases c) is unchanged
On a straight unswept wing, stall occurs at
Ans a) the thick portion at the wing root b) the thick portion at the wing tip c) the thin portion at the wing tip
During a climb from a dive
Ans a) the thrust required is greater than required for level flight
b) the thrust required is lower than for level flight
c) the thrust required is the same as for level flight
When power is off, the aircraft will pitch
Ans a) nose down b) nose up c) trim level
Angle of attack on a down going wing in a roll
Ans a) increases b) decreases c) unaffected
For any given speed, a decrease in aircraft weight, the induced drag will
a) increase Ans b) decrease c) remain the same
The amount of lift generated by a wing is
Ans a) greatest at the root b) greatest at the tip c) constant along the span
Induced Drag is
a) greatest towards the wing root and downwash is greatest at the tip
b) greatest towards the wing tip and downwash is greatest towards the root
Ans c) greatest towards the tip and downwash decreases from tip to root
Induced Drag is
a) equal to profile drag at stalling angle Ans b) equal to profile drag at Vmd c) never equal to profile drag
With an increase in aircraft weight
a) Vmd will be at the same speed b) Vmd will be at a lower speed Ans c) Vmd will be at a higher speed
For a given IAS an increase in altitude will result in
a) no change a) increase
Ans b) decrease
c) remain the same
As the angle of attack of a wing is increased in level flight
a) the Cof G moves aft and the Cof P forward
Ans b) the Cof P and transition point move forward
c) the Cof P moves forward and the stagnation point aft over the upper surface
Stall inducers may be fitted to a wing
a) at the tip to cause the root to stall first
b) at the root to cause the tip to stall first
Ans c) at the root to cause the root to stall first
With increasing altitude pressure decreases and
a) temperature decreases at the same rate as pressure reduces
Ans b) temperature decreases but at a lower rate than pressure reduces
c) temperature remains constant to 8000 ft
The Centre of Pressure is
Ans a) the point on the chord line at which the resultant lift force may be said to act
b) the point of maximum pressure on the under surface of the wing
c) the centre of gravity of the wing
If the angle of attack is increased the Centre of Pressure will
Ans a) move forward b) move rearward c) remain stationary
The optimum angle of attack of an aerofoil is the angle at which
a) the aerofoil produces maximum lift b) the aerofoil produces zero lift
Ans c) the highest lift/drag ratio is produced
A high aspect ratio wing has a
a) increased induced drag Ans b) decreased induced drag c) decreased skin friction drag
Minimum total drag of an aircraft occurs
a) at the stalling speed Ans b) when profile drag equals induced drag c) when induced drag is least
If the weight of an aircraft is increased, the induced drag at a given speed
Ans a) will increase b) will decrease c) will remain the same
The transition point on a wing is the point where
a) the flow separates from the wing surface
Ans b) the boundary layer flow changes from laminar to turbulent
c) the flow divides to pass above and below the wing
The boundary layer of a body in a moving airstream is
Ans a) a thin layer of air over the surface where the air is stationary
b) a layer of separated flow where the air is turbulent
c) a layer of air over the surface where the airspeed is changing from free stream speed to zero speed
A laminar boundary layer will produce
a) more skin friction drag than a turbulent one
Ans b) less skin friction drag than a turbulent one
c) the same skin friction drag as a turbulent one
Longitudinal stability is given by
a) the fin b) the wing dihedral Ans c) the horizontal tailplane
Lateral stability is given by
a) the ailerons Ans b) the wing dihedral c) the horizontal tailplane
Stability about the lateral axis is given by
a) wing dihedral Ans b) the horizontal tailplane c) the ailerons
Sweepback of the wings will
Ans a) increase lateral stability b) decrease lateral stability c) not affect the lateral stability
Dutch Roll is
Ans a) a combined rolling and yawing motion b) a type of slow roll c) primarily a pitching instability
A high wing position gives
Ans a) more lateral stability than a low wing
b) less lateral stability than a low wing
c) the same lateral stability as a low wing
On an aircraft in an unpowered steady speed descent
a) the lift equals the weight b) the weight equals the drag Ans c) the weight equals the resultant of the lift and drag
When an aircraft rolls to enter a turn and power is not increased
a) the lift equals the weight b) the lift is greater than the weight Ans c) the lift is less than the weight
The boundary layer is
a) thickest at the leading edge Ans b) thickest at the trailing edge c) constant thickness from leading to trailing edges
The amount of thrust produced by a jet engine or a propeller can be calculated using
a) Newton’s 1st law Ans b) Newton’s 2nd law c) Newton’s 3rd law
An engine which produces an efflux of high speed will be
a) more efficient Ans b) less efficient c) speed of efflux has no affect on the engine efficiency
When an aircraft with a Cof G forward of the Cof P rolls, the nose of the aircraft will
a) stay level b) rise Ans c) drop
Directional stability may be increased with
a) pitch dampers b) horn balance Ans c) yaw dampers
Lateral stability may be increased with
Ans a) increased lateral dihedral b) increased lateral anhedral c) increased longitudinal dihedral
Longitudinal stability is increased if the
a) CP moves forward of the CG b) Thrust acts on a line below the total drag Ans c) CG is forward of the CP
Wing loading is calculated by weight
Ans a) divided by gross wing area b) divided by lift c) multiplied by gross wing area
Induced drag is
Ans a) inversely proportional to the square of speed b) proportional to speed c) nothing to do with speed
In a bank, the weight is
a) increased b) decreased Ans c) the same
L/D ratio is
a) higher at supersonic cruise speed Ans b) higher at sub sonic speed c) the same
The power required at low altitude for a given IAS is
Ans a) the same as at high altitude b) higher c) lower
If the stall speed is 75 knots what is the same stall speed in mph
a) 75 x 0.87 Ans b) 75 / 0.87 c) 75 / 0.87 x relative density
As the angle of attack increases the stagnation point
a) moves towards the upper surface Ans b) moves towards the lower surface c) does not move
The term pitch-up is due to
Ans a) compressibility effect b) ground effect c) longitudinal instability
In a steady climb at a steady IAS, the TAS is
Ans a) more than IAS b) less than IAS c) the same
An untapered wing will
a) have no yaw effect in banking b) have no change in induced drag in the bank Ans c) stall at the root first
With the ailerons away from the neutral, induced drag is
a) unchanged but profile drag is higher b) higher on the lower wing plus profile drag increases
Ans c) higher on the upper wing plus profile drag increases
The lift drag ratio is
a) higher at mach numbers above supersonic Ans b) higher at sub sonic mach numbers c) the same
The force opposing thrust is
Ans a) drag b) lift c) Weight
Directional stability is about the
Ans a) normal axis b) longitudinal axis c) lateral axis
Lateral stability is about the
Ans a) longitudinal axis b) normal axis c) vertical axis
All the lift can be said to act through the
Ans a) center of pressure b) center of gravity c) normal axis
Longitudinal stability is provided by the
Ans a) horizontal stabilizer b) Vertical stabilizer c) Main plane
The concept of thrust is explained by
a) Newton’s 1st law Ans b) Newton’s 3rd law c) Bernoulli’s theorem
The camber of an aerofoil section is
Ans a) the curvature of the median line of the aerofoil
b) the angle of incidence towards the tip of a wing
c) the angle which the aerofoil makes with the relative airflow
If the aircraft turns and side-slips
a) the sweepback of the wing will correct the sideslip
Ans b) the dihedral of the wing will correct the sideslip
c) the keel surface will correct the sideslip
Movement of an aircraft about its lateral axis
Ans a) is pitching b) is rolling c) is yawing
Induced drag
a) is caused by skin friction
b) results from disturbed airflow in the region of mainplane attachments
Ans c) is associated with the lift generated by an aerofoil
The centre of pressure is
Ans a) the point on the chord line through which the total resultant lift force on the aerofoil may be said to act
b) the point of maximum pressure on the undersurface of a mainplane
c) the point at which the four forces acting on an aircraft are said to act
At what altitude is tropopause
a) 63,000 ft. Ans b) 36,000 ft. c) 57,000 ft.
What approximate percentage of oxygen is in the atmosphere
a) 12% Ans b) 21% c) 78%
Which has the greater density
Ans a) air at low altitude b) air at high altitude c) it remains constant
As air flows over the upper cambered surface of an aerofoil, what happens to velocity and pressure?
a) Velocity decreases, pressure decreases b) Velocity increases, pressure increases Ans c) Velocity increases, pressure decreases
What is the force that tends to pull an aircraft down towards the earth?
a) Drag b) Thrust Ans c) Weight
Which of the following act in opposition to forward movement?
a) Lift b) Gravity Ans c) Drag
The angle at which the chord line of the aerofoil is presented to the airflow is known as
Ans a) angle of attack b) angle of incidence c) resultant
The imaginary straight line which passes through an aerofoil section from leading edge to trailing edge is called
a) centre of pressure b) the direction of relative airflow Ans c) the chord line
What is the angle between the chord line of the wing, and the longitudinal axis of the aircraft, known as
a) angle of attack Ans b) angle of incidence c) angle of dihedral
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
Ans a) aircraft stability b) aircraft instability c) aircraft stall
Directional control is provided by
a) horizontal stabilizer Ans b) rudder c) elevator
About which axis of the aircraft does a rolling motion take place?
a) Normal axis Ans b) Longitudinal axis c) Lateral axis
Which motion happens about the lateral axis?
Ans a) Pitching b) Yawing c) Rolling
Wing tip vortices create a type of drag known as
a) form drag Ans b) induced drag c) profile drag
Which of the following describes the “Empennage”?
a) Nose section of an aircraft, including the cockpit
Ans b) Tail section of the aircraft, including fin, rudder, tail plane and elevators
c) The wings, including the ailerons
At what altitude does stratosphere commence approximately?
a) Sea level Ans b) 63,000 ft c) 36,000 ft
When an aircraft is in straight and level unaccelerated flight, which of the following is correct?
Ans a) Lift and weight are equal, and thrust and drag are equal
b) Lift greater than weight, and thrust greater than drag
c) Lift greater than weight, and thrust is less than drag
As the angle of attack is increased (up to the stall point), which of the following is correct?
a) Pressure difference between top and bottom of the wing increases
b) Lift increases Ans c) Both a) and b) are correct
The fin gives stability about which axis?
a) Lateral axis Ans b) Normal axis c) Longitudinal axis
What is the horizontal movement of the nose of the aircraft called?
a) Rolling movement b) Pitching movement
Ans c) Yawing movement
What type of drag, depends on the smoothness of the body, and surface area over which the air flows?
a) Parasite drag b) Form drag Ans c) Skin friction drag
if the nose of the aircraft is rotated about its lateral axis, what is its directional movement?
a) Turning to the left or right b) Rolling or banking to the left or right Ans c) Climbing or diving
When air flow velocity over an upper cambered surface of an aerofoil decreases, what takes place?
Ans a) Pressure increases, lift decreases
b) Pressure increases, lift increases c) Pressure decreases, lift increases
When an aircraft stalls
a) lift and drag increase b) lift increases and drag decreases
Ans c) lift decreases and drag increases
Wing loading is
a) the maximum all up weight multiplied by the total wing area
Ans b) the maximum all up weight divided by the total wing area
c) the ratio of the all up weight of the aircraft to its basic weight
An aircraft wing with an aspect ration of 6:1 is proportional so that
a) the mean chord is six times the thickness
Ans b) the wing span is six times the mean chord
c) the wing area is six times the span
On a swept wing aircraft if both wing tip sections lose lift simultaneously the aircraft will
a) Roll Ans b) pitch nose up c) Pitch nose down
Lift on a delta wing aircraft
Ans a) increases with an increased angle of incidence (angle of attack)
b) Decreases with an increase in angle of incidence (angle of attack)
c) Does not change with a change in angle of incidence (angle of attack)
On a straight wing aircraft, stall commences at the
Ans a) root on a high thickness ratio wing
b) Tip on a high thickness ratio wing
c) Tip on a low thickness ratio wing
On a high wing aircraft in a turn
a) The up-going wing loses lift causing a de-stabilizing effect
Ans b) the down-going wing gains lift causing a stabilizing effect
c) The down-going wing loses lift causing a de-stabilizing effect
For the same angle of attack, the lift on a delta wing
a) is greater than the lift on a high aspect ratio wing
Ans b) is lower than the lift on a high aspect ratio wing
c) Is the same as the lift on a high aspect ratio wing
The ISA?
a) Is taken from the equator
b) Is taken from 45 degrees latitude
Ans c) assumes a standard day
At higher altitudes as altitude increases, pressure
a) Decreases at constant rate
b) Increases exponentially
Ans c) decreases exponentially
The thrust-drag couple overcomes the lift-weight couple. What direction of force is required to be produced by the tail of the aircraft to maintain straight and level flight
Ans a) upwards b) Downwards c) Sideways
When the pressure is half of that at sea level, what is the altitude?
a) 12,000 ft. b) 8,000 ft. Ans c) 18,000 ft.
During a turn, the stalling angle
a) Increases b) Decreases Ans c) remains the same
If gauge pressure on a standard day at sea level is 25 PSI, the absolute pressure is
a) 10.3 PSI b) 43.8 PSI Ans c) 39.7 PSI
The C of G moves in flight. The most likely cause of this is
a) Movement of passengers
b) Movement of the center of pressure
Ans c) Consumption of fuel and oils
The C of P is the point where
a) All the forces on an aircraft act
b) The three axis of rotation meet
Ans c) the lift can be said to act
The three axis of an aircraft act through the
Ans a) C of G b) C of P c) Stagnation point
Pressure decreases
Ans a) proportionally with a decrease in temperature
b) Inversely proportional to temperature
c) Pressure and temperature are not related
As air gets colder, the service ceiling of an aircraft
a) Reduces Ans b) increases c) Remains the same
What is sea level pressure?
Ans a) 1013.2 mb b) 1012.3 mb c) 1032.2 mb
When the weight of an aircraft increases, the minimum drag speed
a) Decreases Ans b) increases c) Remains the same
An aircraft will have
a) Less gliding distance if it has more payload
b) More gliding distance if it has more payload
Ans c) the same gliding distance if it has more payload
When an aircraft experiences induced drag
Ans a) air flows under the wing span wise towards the tip and on top of the wing span wise towards the root
b) Air flows under the wing span wise towards the root and on top of the wing span wise towards the tip
c) Neither a) or b) since induced drag does not caused by span wise flow
At stall, the wingtip stagnation point
Ans a) moves toward the lower surface of the wing
b) Moves toward the upper surface of the wing c) Doesn’t move
How does IAS at the point of stall vary with height?
Ans a) It is practically constant b) It increases c) It decreases
The rigging angle of incidence of an elevator is
Ans a) the angle between the mean chord line and the horizontal in the rigging position
b) The angle between the bottom surface of the elevator and the horizontal in the rigging position
c) The angle between the bottom surface of the elevator and the longitudinal datum
What is the lapse rate with regard to temperature?
Ans a) 1.98oC per 1000 ft. b) 1.98oF per 1000 ft. c) 4oC per 1000 ft.
What happens to load factor as you decrease turn radius?
a) It increases Ans b) It decreases c) It remains constant
If you steepen the angle of a banked turn without increasing airspeed or angle of attack, what will the aircraft do?
a) It will remain at the same height
Ans b) It will sideslip with attendant loss of height c) It will stall
An aircraft wing tends to stall first at
a) the tip due to a higher ratio thickness/chord
b) the tip due to a lower ratio thickness/chord Ans c) the root due to a higher ratio thickness/chord
Dihedral wings combat instability in
a) pitch b) yaw Ans c) sideslip
To stop aircraft decreasing in height during a sideslip, the pilot can
Ans a) advance the throttle
b) pull back on the control column
c) adjust the rudder position
What control surface movements will make an aircraft fitted with ruddervators yaw to the left?
Ans a) Left ruddervator lowered, right ruddervator raised
b) Right ruddervator lowered, left ruddervator raised
c) Both ruddervator raised
When a leading edge slat opens, there is a gap between the slat and the wing. This is
a) To allow it to retract back into the wing
Ans b) To allow air through to re-energize the boundary layer on top of the wing
c) To keep the area of the wing the same
Which of the following is true?
a) Lift acts at right angles to the wing chord line and weight acts vertically down
Ans b) Lift acts at right angles to the relative airflow and weight acts vertically down
c) Lift acts at right angles to the relative air flow and weight acts at right angles to the aircraft centre line
If the wing tips stall before the root on a swept wing aircraft, the aircraft will
a) roll Ans b) pitch nose up c) pitch nose down
Lift on a delta wing aircraft
Ans a) increases with an increased angle of incidence (angle of attack)
b) decreases with an increase in angle of incidence (angle of attack)
c) does not change with a change in angle of incidence (angle of attack)
On a straight wing aircraft, stall commences at the
Ans a) root on a high thickness ratio wing
b) tip on a high thickness ratio wing
c) tip on a low thickness ratio wing
On a high wing aircraft in a turn
a) the up-going wing loses lift causing a de-stabilizing effect
Ans b) the down-going wing gains lift causing a stabilizing effect c) the down-going wing loses lift causing a de-stabilizing effect
For the same angle of attack, the lift on a delta wing
a) is greater than the lift on a high aspect ratio wing
Ans b) is lower than the lift on a high aspect ratio wing
c) is the same as the lift on a high aspect ratio wing
The ISA
a) is taken from the equator
Ans b) is taken from 45 degrees latitude
c) assumes a standard day
As altitude increases, pressure
a) decreases at constant rate b) increases exponentially Ans c) decreases exponentially
The thrust-drag couple overcomes the lift-weight couple. What direction of force is required to be produced by the tail of the aircraft to maintain straight and level flight?
Ans a) Upwards b) Downwards c) Sideways
When the pressure is half of that at sea level, what is the altitude?
a) 12,000 ft b) 8,000 ft Ans c) 18,000 ft
During a turn, the stalling angle
a) increases b) decreases Ans c) remains the same
The vertical fin of a single engined aircraft is
Ans a) parallel with both the longitudinal axis and vertical axis
b) parallel with the longitudinal axis but not the vertical axis
c) parallel with the vertical axis but not the longitudinal axis
Aircraft flying in the transonic range most often utilize
Ans a) sweptback wings b) advanced supercritical airfoils
c) high wings
Which type of flap changes the area of the wing?
Ans a) Fowler b) Split c) Slotted
Forward swept wings tend to stall at the root first so the aircraft retains lateral control, so why are they never used on passenger aircraft?
a) Because the wing tips wash in at high wing loads
b) Because the wing tips wash out at high wing loads
Ans c) Because at high loads their angle of incidence increases and the loads imposed on the wing can increase until they destroy it
What happens to air flowing at the speed of sound when it enters a converging duct?
a) Velocity decreases, pressure and density increase
b) Velocity increases, pressure and density decreases
Ans c) Velocity, pressure and density increase
As the angle of attack of an airfoil increases the centre of pressure
Ans a) moves forward b) moves aft c) remains stationary
An aircraft, which is longitudinally stable, will tend to return to level flight after a movement about which axis?
Ans a) Pitch b) Roll c) Yaw
Vapour trails from the wingtips of an aircraft in flight are caused by
Ans a) low pressure above the wing and high pressure below the wing causing vortices
b) high pressure above the wing and low pressure below the wing causing vortices
c) low pressure above the wing and high pressure below the wing causing a temperature rise
Vortex generators on the wing are most effective at
a) high speed b) low speed Ans c) high angles of attack
The chord line of a wing is a line that runs from
Ans a) the centre of the leading edge of the wing to the trailing edge
b) half way between the upper and lower surface of the wing
c) one wing tip to the other wing tip
The angle of incidence of a wing is an angle formed by lines
Ans a) parallel to the chord line and longitudinal axis
b) parallel to the chord line and the lateral axis
c) parallel to the chord line and the vertical axis
The centre of pressure of an aerofoil is located
Ans a) 30 - 40% of the chord line back from the leading edge
b) 30 - 40% of the chord line forward of the leading edge
c) 50% of the chord line back from the leading edge
Compressibility effect is
a) drag associated with the form of an aircraft
b) drag associated with the friction of the air over the surface of the aircraft
Ans c) the increase in total drag of an airfoil in transonic flight due to the formation of shock waves
Lateral control of an aircraft at high angle of attack can be maximised by using
a) fences Ans b) vortex generators c) wing slots
Stall strips are always
a) made of metal Ans b) on the leading edge of a wing c) fitted forward of the ailerons
Stall strips
Ans a) cause the wing root to stall b) cause the wing tip to stall
c) cause the wings to stall symmetrically
Due to the interference of the airflow on a high wing aircraft between the fuselage and the wings, the lateral stability of the aircraft in a gusty wind situation will cause
a) the upper wing to increase its lift Ans b) the upper wing to decrease its lift
c) the lower wing to decrease its lift
Slats
Ans a) reduce the stall speed
b) reduce the tendency of the aircraft to Yaw
c) decrease the aerofoil drag at high speeds
What is the temperature lapse rate for aircraft flying below 36,000 feet altitude?
a) 1°C per 1000 feet b) 3°C per 1000 feet Ans c) 2°C per 1000 feet
For a pressure of 25lbs/in² at sea level, what is the absolute pressure?
Ans a) 39.7 lbs/in² b) 49.7 lbs/in² c) 10.3 lbs/in
An aircraft banks into a turn. No change is made to the airspeed or angle of attack. What will happen?
Ans a) The aircraft enters a side slip and begins to lose altitude
b) The aircraft turns with no loss of height
c) The aircraft yaws and slows down
The relationship between induced drag and airspeed is
a) directly proportional to the square of the speed
Ans b) inversely proportional to the square of the speed
c) directly proportional to speed
What is the definition of Angle of Incidence?
a) The angle the underside of the mainplane or tailplane makes with the horizontal
b) The angle the underside of the mainplane or tailplane makes with the longitudinal datum line
Ans c) The angle the chord of the mainplane or tailplane makes with the horizontal
What is Boundary Layer?
a) Separated layer of air forming a boundary at the leading edge
b) Turbulent air moving from the leading edge to trailing edge
Ans c) Sluggish low energy air that sticks to the wing surface and gradually gets faster until it joins the free stream flow of air
The normal axis of an aircraft passes through
Ans a) the centre of gravity b) a point at the center of the wings c) at the centre of pressure
On a high winged aircraft, what effect will the fuselage have on the up-going wing?
Ans a) The up-going wing will have a decrease in angle of attack and therefore a decrease in lift
b) The down-going will have a decrease in angle of attack and therefore a decrease in lift
c) The up-going wing will have an increase in angle of attack and therefore a decrease in lift
What is the collective term for the fin and rudder and other surfaces aft of the centre of gravity that helps directional stability?
Ans a) Effective keel surface b) Empennage c) Fuselage surfaces
Temperature above 36,000 feet will
a) decrease exponentially Ans b) remain constant c) increase exponentially
A decrease in incidence toward the wing tip may be provided to
a) prevent adverse yaw in a turn
b) prevent spanwise flow in maneuvers Ans c) retain lateral control effectiveness at high angles of attack
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