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080 – PRINCIPLES OF FLIGHT
081-01

SUBSONIC AERODYNAMICS
081-01-01 Basics, laws and definitions

2625
...
Assuming ISA conditions, which statement with respect to the climb is correct?
A – At constant TAS the Mach number decreases
B – At constant Mach number the IAS increases
C – At constant IAS the TAS decreases
D – At constant IAS the Mach number increases
Ref: AIR: atpl, cpl;
Ans: D
3848
...
The point about which the wing pitching moment is independent of angle of
attack is called:
A – the pitching centre
B – the centre of gravity
C – the centre of pressure
D – the aerodynamic centre
Ref: AIR: atpl, cpl;
Ans: D
4184
...
The unit of density is:
A – Bar
B – psi
C – kg/cm2
D – kg/m3
Ref: AIR: atpl, cpl;
Ans: D
4199
...
The term angle of attack is defined as:
A – the angle that determines the magnitude of the lift force
B – the angle between the wing chord line and the relative wind
C – the angle between the relative airflow and the horizontal axis
D – the angle between the wing and tailplane incidence
Ref: AIR: atpl, cpl;
Ans: B
4202
...
At a constant IAS, induced drag is affected by:
A – aircraft weight
B – changes in thrust
C – angle between chord line and longitudinal axis
D – wing location
Ref: AIR: atpl, cpl;
Ans: A
4213
...
At a constant CAS when flying below sea level an aircraft will have:
A – a higher TAS than at sea level
B – a lower TAS than at sea level at ISA conditions
C – the same TAS as at sea level
D – the same TAS, but an increased IAS
Ref: AIR: atpl, cpl;
Ans: B
4232
...
The units of wing loading (i) W / S and (ii) dynamic pressure q are:
A – (i) N/m2; (ii) kg/m2
B – (i) kg/m; (ii) N/m2
C – (i) N/m; (ii) kg
D – (i) N/m2; (ii) N/m2
Ref: AIR: atpl, cpl;
Ans: D
4252
...
The units of the density of the air (i) and the force (ii) are:
A – (i) kg/m3; (ii) N
B – (i) kg/m3; (ii) kg
C – (i) N/m3; (ii) N
D – N/kg; (ii) kg
Ref: AIR: atpl, cpl;
Ans: A
7643
...
The dynamic pressure in the undisturbed flow and in the throat are equal
2
...
A symmetrical aerofoil section at CL = 0 will produce?
A – A negative (nose down) pitching moment
B – A positive (nose up) pitching moment
C – Zero pitching moment
D – No aerodynamic force
Ref: AIR: atpl, cpl;
Ans: C
7650
...
What is the SI unit that results from multiplying kg and m/s2?
A – Joule
B – Psi
C – Newton
D – Watt
Ref: AIR: atpl, cpl;
Ans: C
7658
...
What happens to total drag when accelerating from CL MAX to maximum
speed?
A – Increases
B – Increases then decreases
C – Decreases
D – Decreases then increases
Ref: AIR: atpl, cpl;
Ans: D
7689
...
4 times the lift
B - twice the lift
C – four times the lift
D – the same lift
Ref: AIR: atpl, cpl;
Ans: D

7691
...
Which of the following is the correct description of the method for measuring
the dihedral angle?
A – The angle between the wing plane and the horizontal
B – The angle between a line which passes through the 25% wing chord and
the horizontal axis
C – The angle between the 25% chord line and the horizontal axis
D – The angle between 25% chord and the lateral axis
Ref: AIR: atpl, cpl;
Ans: A
7700
...
What phenomena causes induced drag?
A – Wing tip vortices
B – Wing tanks
C – The increased pressure at the leading edge
D – The spanwise flow, inward below the wing and outward above
Ref: AIR: atpl, cpl;
Ans: A

7707
...
The following unit of measurement kgm/s? is expressed in the SI-system as:
A – Pascal
B – Newton
C – Joule
D – Watt
Ref: AIR: atpl, cpl;
Ans: B
7715
...
Which of the following is the speed that would activate the stick shaker:
A – 1
...
05 VS
C – 1
...
If the IAS is increased by a factor of 4, by what factor would the drag increase?
A–4
B–8
C – 12
D – 16
Ref: AIR: atpl, cpl;
Ans: D
7724
...
What are the correct SI units for density and force?
A – KG/N, Nm3
B – N/m3, Kg
C – Kg/m3, Newtons
D – KG/m3, Kg
Ref: AIR: atpl, cpl;
Ans: C
7738
...
At a given CAS an aircraft flying below sea level will have:
A – the same TAS as at sea level
B – a lower TAS than at sea level
C – a higher TAS than at sea level
D – the same TAS as at sea level but an increased IAS
Ref: AIR: atpl, cpl;
Ans: B
7751
...
A line connecting the leading and trailing edge midway between the upper and
lower surface of an aerofoil
...
In recovery from a spin:
A – ailerons should be kept neutral
B – airspeed increases
C – ailerons used to stop the spin
D – ruddeer and ailerons used against the direction of spin rotation
Ref: AIR: atpl, cpl;
Ans: A

7761
...
What is the SI unit which results from multiplying kg and m/s squared?
A – Newton
B – Psi
C – Joule
D – Watt
Ref: AIR: atpl, cpl;
Ans: A
7775
...
The angle between the chord line of the wing and the longitudinal axis of the
airplane is known as the angle of:
A – attack
B – relative wind
C – incidence
D – dihedral
Ref: AIR: atpl, cpl;
Ans: C

7793
...
In subsonic flight, which is correct for VMD?
A – Parasite drag greater than induced drag
B – CL and CD are minimum
C – Best glide range achieved
D – Best endurance speed for a piston engine
Ref: AIR: atpl, cpl;
Ans: C
7803
...
The aspect ratio of the wing:
A – is the ratio between the wing span and the root chord
B – is the ratio between the wing span and the mean geometric chord
C – is the ratio between the tip chord and the wing span
D – is the ratio between chord and root chord
Ref: AIR: atpl, cpl;
Ans: B

7812
...
Bernoullis Theorem states:
A – dynamic pressure increase and static pressure increase
B – dynamic pressure increase and static pressure decrease
C – dynamic pressure is maximum at stagnation point
D – zero pressure at zero dynamic pressure
Ref: AIR: atpl, cpl;
Ans: B
7821
...
The true airspeed (TAS) is:
A – higher than the speed of the undisturbed airstream about the aeroplane
B – lower than the indicated airspeed (IAS) at ISA conditions and altitudes
below sea level
C – equal to the IAS, multiplied by the air density at sea level
D – lower than the speed of the undisturbed airstream about the aeroplane
Ref: AIR: atpl, cpl;
Ans: B

7835
...
What effect on stall speed do the following have?
A – Increased anhedral increases stall speed
B – Fitting a T tail will reduce stall speed
C – Increasing sweepback decreases stall speed
D – Decreasing sweep angle decreases stall speed
Ref: AIR: atpl, cpl;
Ans: D
7839
...
In a symmetrical airfoil the mean camber line is?
A – A line joining points of mean camber along the wing
B – A line joining points of maximum camber along the wing
C – A curve co-incident with the top surface of the airfoil
D – A straight line co-incident with the chord line
Ref: AIR: atpl, cpl;
Ans: D

7854
...
Considering a positive cambered aerofoil, the pitch moment when Cl=0 is:
A – negative (pitch-down)
B – equal to zero
C – infinite
D – positive (pitch-up)
Ref: AIR: atpl, cpl;
Ans: A
7887
...
Longitudinal dihedral is:
A – the difference between the wing and tail angle of sweep
B - the difference between the wing and tail angle of incidence
C – when the wing has anhedral and the tail dihedral
D – the difference between the wing and tail dihedral angles
Ref: AIR: atpl, cpl;
Ans: B

7895
...
Which of the following statements are correct?
A – Drag acts in the same direction as the relative airflow and lift
perpendicular to it
B – Lift acts at right angles to the top surface of the wing and drag acts at right
angles to lift
C – Drag acts parallel to the chord and opposite to the direction of motion of
the aircraft and lift acts perpendicular to the chord
D – Lift acts perpendicular to the horizontal and drag parallel in a rearwards
direction
Ref: AIR: atpl, cpl;
Ans: A
7909
...
The velocity of the stream in the tube is V
...
Static pressure acts:
A – parallel to airflow
B – parallel to dynamic pressure
C – in all directions
D – downwards
Ref: AIR: atpl, cpl;
Ans: C

7925
...
Dihedral of the wing is:
A – the angle between the 0
...
25 chord line of the wing and the lateral axis
D – the angle between the 0
...
Which one of the following statements about Bernoullis theorem is correct?
A – The dynamic pressure is maximum in the stagnation point
B – The dynamic pressure decreases as static pressure decreases
C – The total pressure is zero when the velocity of the stream is zero
D – The dynamic pressure increases as static pressure decreases
Ref: AIR: atpl, cpl;
Ans: D
7952
...
Its mean chord
would be:
A – 4 feet
B – 10 feet
C – 7
...
5 feet
Ref: AIR: atpl, cpl;
Ans: A

7966
...
The angle of attack (aerodynamic angle of incidence) of an aerofoil is the
angle between the:
A – bottom surface and the chord line
B – chord line and the relative undisturbed airflow
C – bottom surface and the Horizontal
D – bottom surface and the relative airflow
Ref: AIR: atpl, cpl;
Ans: B
15609
...
a
B – a = F
...
a
Ref: AIR: atpl, cpl;
Ans: D
15610
...
The Cl – alpha curve of a positive cambered aerofoil intersects with the
vertical axis of the Cl – alpha graph:
A – in the origin
B – below the origin
C – nowhere
D – above the origin
Ref: AIR: atpl, cpl;
Ans: D
15695
...
Its flight Mach range between low-speed buffering
and high-speed buffering goes from:
A – M = 0
...
84
B – M = 0
...
84
C – M = 0
...
84
D – M = 0
...
84
Ref: AIR: atpl, cpl;
Ans: D
15697
...
The correct drag formula is:
A – D = CD ½ RHO V? S
B – D = CD 2 RHO V? S
C – D = CD ½ RHO V S
D – D = CD ½ 1/RHO V? S
Ref: AIR: atpl, cpl;
Ans: A

15736
...
The total pressure is:
A – can be measured in a small hole in a surface, parallel to the local stream
B – static pressure plus the dynamic pressure
C – static pressure minus the dynamic pressure
D – ½ rho V2
Ref: AIR: atpl, cpl;
Ans: B
15738
...
The relative thickness of an aerofoil is expressed in:
A – degrees cross section tail angle
B - % chord
C – camber
D – meters
Ref: AIR: atpl, cpl;
Ans: B

15750
...
High Aspect Ratio, as compared with low Aspect Ratio, has the effect of:
A – increasing lift and drag
B – increasing induced drag and decreasing critical angle of attack
C – decreasing induced drag and critical angle of attack
D – increasing lift and critical angle of attack
Ref: AIR: atpl, cpl;
Ans: C
15760
...
Lift and drag on an aerofoil are vertical respectively parallel to the:
A – horizon
B – relative wind/airflow
C – chord line
D – longitudinal axis
Ref: AIR: atpl, cpl;
Ans: B

15775
...
For an aircraft in level flight, if the wing centre of pressure is aft of the centre
of gravity and there is no thrust/drag couple, the tailplane load must be:
A – upward
B – unknown-insufficient information has been provided
C – downward
D – zero
Ref: AIR: atpl, cpl;
Ans: C
16659
...
In straight and level flight the centre of pressure is behind the centre of
gravity
...
The service ceiling of an aircraft is:
A – the altitude where rate of climb is zero
B – the highest altitude permitted for flight because of manoeuvre capability
C – the altitude where a low specific rate of climb is achieved
D – the altitude above which cruising speed cannot be maintained
Ref: AIR: atpl, cpl;
Ans: C
16671
...
an aerofoil is cambered when:
A – the upper surface of the aerofoil is curved
B – the chord line is curved
C – the line, which connects the centres of all inscribed circles, is curved
D – the maximum thickness is large compared with the length of the chord
Ref: AIR: atpl, cpl;
Ans: C
21036
...
Bernoulli’s equation is:
(note: rho is density; pstat is static pressure; pdyn is dynamic pressure; ptot is
total pressure)
A – ptot + 1rho * TAS2 = constant
B – ptat + 1rho * IAS2 = constant
C – pdyn + 1rho * IAS2 = constant
D – pstat + 1rho * TAS2 = constant
Ref: AIR: atpl, cpl;
Ans: D
21039
...
an increase in temperature of the flow at a constant value of V
will:
A – increase the mass flow when the tube is divergent in the direction of the
flow
B – increase the mass flow
C – not affect the mass flow
D – decrease the mass flow
Ref: AIR: atpl, cpl;
Ans: D
21077
...
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
A – Ps decreases, Pdyn increases, static temperature increases
B – Ps increases, Pdyn decreases, Ptot remains constant
C – Ps decreases, Pdyn increases, Ptot remains constant
D – Ps decreases, Ptot increases, static temperature decreases
Ref: AIR: atpl, cpl;
Ans: C
21108
...
The angle of attack of an aerofoil section is the angle between the:
A – bottom surface and the chord line
B – bottom surface and the horizontal
C – bottom surface and the relative airflow
D – chord line and the relative undisturbed airflow
Ref: AIR: atpl, cpl;
Ans: D
21116
...
The Sl unit of measurement for pressure is:
A – lb/gal
B – kg/m3
C – N/m2
D – bar/dm2
Ref: AIR: atpl, cpl;
Ans: C
21130
...
The unit of measurement for density is:
A – kg/m3
B – psi
C – kg/cm2
D – bar
Ref: AIR: atpl, cpl;
Ans: A
21165
...
Which of the following statements about a venture in a sub sonic airflow are
correct?
1
...
the total pressures in the undisturbed flow and in the throat are equal
A – 1 is incorrect and 2 is correct
B – 1 and 2 are correct
C – 1 is correct and 2 is incorrect
D – 1 and 2 are incorrect
Ref: AIR: atpl, cpl;
Ans: A
23200
...
The input connections to an Air Speed Indicator are from:
A – a static source only
B – a pitot source only
C – both pitot and static sources
D – pitot and static sources and outside air temperature sensor
Ref: AIR: atpl, cpl;
Ans: C
23202
...
For a cambered aerofoil which of the following statements is correct:
A – it will give lift at small negative angles of attack
B – at negative angles of attack it will produce negative lift only
C – it will give lift at positive angles of attack only
D – it will give negative lift at small positive angles of attack
Ref: AIR: atpl, cpl;
Ans: A
23205
...
As air flows into the converging section of a venture:
A – static pressure decreases, velocity increases, mass flow decreases
B – static pressure increases, velocity decreases, mass flow is constant
C – static pressure decreases, velocity increases, mass flow is constant
D – static pressure decreases, velocity decreases, mass flow decreases
Ref: AIR: atpl, cpl;
Ans: C
23208
...
The chord line of an aerofoil is:
A – a line from wing tip to wing tip
B – a line from the leading edge to trailing edge equidistant from the upper
and lower surfaces
C – a straight line joining the centre of curvature of the leading and trailing
edges
D – a horizontal line tangential to the wing surface
Ref: AIR: atpl, cpl;
Ans: C
23210
...
A symmetrical aerofoil at zero degree angle of attack will, in level flight
produce:
A – most of its lift on the lower surface
B – most of its lift on the upper surface
C – the same amount of lift on the upper and lower surfaces
D – zero lift
Ref: AIR: atpl, cpl;
Ans: D
23227
...
At higher elevation airports the pilot should know that indicated airspeed:
A – will be unchanged, but ground speed will be faster
B – will be higher, but ground speed will be unchanged
C – should be increased to compensate for the thinner air
D – to maintain the required dynamic pressure the indicated airspeed should
be increased
Ref: AIR: atpl, cpl;
Ans: A
23236
...
Effective angle of attack is the:
A – angle between the chord line and the mean direction of a non-uniform
disturbed air stream
B – angle between the relative airflow and the chord line
C – angle between the chord line and the fuselage horizontal datum
D – angle between the fuselage horizontal datum and the chord line of the
horizontal stabiliser
Ref: AIR: atpl, cpl;
Ans: A
23240
...
If the speed of an aircraft is 100 miles per hour, its speed in knots would be:
A – 87 kts
B – 115 kts
C – 70 kts
D – 65 kts
Ref: AIR: atpl, cpl;
Ans: A
23242
...
5 degrees C at 26
...
5 degrees F at 36
...
5 degrees C at 36
...
5 degrees C at 36
...
In ISA pressure decreases:
A – at a constant rate as altitude increases
B – at a rate of milibar per 30 ft at low altitudes
C – at a rate of 0
...
If an aircraft is descending at 500 ft/min from 5000 ft altitude, the rate of
pressure increase outside the aircraft is:
A – greater than the rate of pressure increase outside an aircraft descending at
500 ft/min from 15000 ft to 10000 ft
B – less than the rate of pressure increase outside an aircraft descending at 500
ft/min from 15000 ft to 10000 ft
C – equal to the rate of pressure increase outside an aircraft descending at
5000 ft/min at any altitude
D – the rate of change will be the same
Ref: AIR: atpl, cpl;
Ans: A

23248
...
A wing has a span of 64m and an area of 525 square metres
...
8 m
B – 0
...
2 m
D – 3
...
A wing would be said to be swept back if:
A – the wing tips were lower than the wing roots
B – the tip chord was less than the root chord
C – the quarter chord line was inclined backwards from the lateral axis
D – the tip incidence was less than the root incidence
Ref: AIR: atpl, cpl;
Ans: C
23253
...
A wing with a high thickness : chord ratio would be suitable for:
A – an aircraft with a high wing loading
B – an aircraft intended to operate at high speed
C – an aircraft intended to operate at low speed
D – an aircraft designed to operate at extremely high altitudes
Ref: AIR: atpl, cpl;
Ans: C
23272
...
The distance
in the moment is merely a leverage and no movement is involved
B – the product of a force and the distance through which it moves
C – the product of the application of a force
D – the vector quantity of a lever
Ref: AIR: atpl, cpl;
Ans: A
23275
...
The position error of an ASI results from:
A – mechanical differences in individual instruments
B – the difference in air density from sea level ISA ensity
C – the effects of the airflow around the static vent and pitot head
D – the fact that air becomes more compressible at high speeds
Ref: AIR: atpl, cpl;
Ans: C

23277
...
If the atmospheric pressure is less than standard:
A – take-off distance would be reduced
B – take-off distance would be increased
C – take-off distance would not be affected
Ref: AIR: atpl, cpl;
Ans: B
23281
...
The aspect ratio
is:
A – 3:1
B – 10:1
C – 30:1
D – 9:1
Ref: AIR: atpl, cpl;
Ans: A
23282
...
The most correct list of 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
C – angle of attack, velocity, wing area, aerofoil section, air density
D – incidence, TAS, wing plan, leading edge radius and thrust
Ref: AIR: atpl, cpl;
Ans: C
23287
...
The aspect
ratio is:
A – 5 to 1
B – 30 to 1
C – 180 to 1
D – 6 to 1
Ref: AIR: atpl, cpl;
Ans: A
23289
...
A swept wing:
A – produces more lift at a given angle of attack than an equivalent straight
wing
B – reaches the critical angle of attack before an equivalent straight wing
C – produces less lift at a given angle of attack than an equivalent straight
D – produces zero lift at zero angle of attack
Ref: AIR: atpl, cpl;
Ans: C

23310
...
87
B – divide the knots by 0
...
87 and divide by the relative density
D – divide the knots by 8
...
The aerodynamic centre is the point on the chord line where:
A – drag acts
B – the sum of all aerodynamic forces act
C – the geometric centre of the wing is located
D – the pitching moment remains constant throughout changes in angle of
attack within the normal range
Ref: AIR: atpl, cpl;
Ans: D
23313
...
Airflow, the product of the aircraft moving forwards, parallel to and in the
opposite direction to the flight path, its pressure, temperature and relative
velocity unaffected by the presence of the aircraft:
A – is known as static pressure
B – is known as dynamic pressure
C – is known as total pressure
D – is known as relative airflow
Ref: AIR: atpl, cpl;
Ans: D

23316
...
The density of air may be measured in:
A – kg/square metre
B – milibars
C – kg/cubic metre
D – Newton’s per cubic metre
Ref: AIR: atpl, cpl;
Ans: C
23343
...
Density of the atmosphere will:
A – increase with rising humidity
B – decrease with rising humidity
C – remain unaffected by changes in humidity
D – decrease with reduced humidity
Ref: AIR: atpl, cpl;
Ans: B

23488
...
If air is assumed to be incompressible, this means:
A – there will be no change in pressure when the speed of the airflow is
changed
B – there will be no change of density due to change of pressure
C – the density will only change with speed at supersonic speed
D – pressure changes will only occur at very high speeds
Ref: AIR: atpl, cpl;
Ans: B
23579
...
What is the SI unit for density?
A – mV2
B – kg/cm2
C – kg-m
D – kg/m3
Ref: AIR: atpl, cpl;
Ans: D

23611
...
Which of the following is the equation for power?
A – N/m
B – NM/s
C – Pa/s2
D – Kg/m/s2
Ref: AIR: atpl, cpl;
Ans: B
23734
...
The aerodynamic centre is:
A – the point where the CG meets the lateral axis
B – the point where all changes in the magnitude of the lift

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