Here are the Aerodynamics Board Exam Questions reviewers in the Philippines and from Oxford, EASA, Volare, and other references.
NOTE: The last part of each item is the right answer.
1. density decreases, true speed of aircraft ___:
Increases
As air density decreases, the true airspeed of an aircraft increases due to the
reduced AIR RESISTANCE.
The aircraft needs to move faster to generate the same amount of lift. This relationship is why aircraft fly faster at higher altitudes, where the air is less dense.
2. 8. 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.
C. High temperature with high humidity.
d.
Low temperature with high humidity.: C. High temperature with high humidity.
True airspeed (TAS) represents the true speed of an airplane through the air. As air
temperature and humidity increase, the density of the air decreases. As air density
decreases, true airspeed increases. Therefore, high temperature with high humidity
will cause an aircraft’s landing speed to be greatest.
3. 18. Frost covering the upper surface of an airplane wing will usually cause
a. The airplane to stall at an angle of attack that is higher than normal
b. The airplane to stall at an angle of attack that is lower than normal
c. Drag factors so large that sufficient speed cannot be obtained for take off
d. Coefficient of drag to increase abruptly: b. The airplane to stall at an angle of
attack that is lower than normal
Magsstall agad
See CL a curve
4. 24. Recovery from a stall in any airplane becomes more difficult when its
Center of gravity moves aft
Center of gravity moves forward
Elevator trim is adjusted nose down Rudder travel is improperly adjusted: –
Center of gravity moves aft
If CG at aft (tail heavy) – tail force cant do downwards
Higher moment (high distance of CP and CG) = mas mahirap macontrol
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5. 26. If airspeed is increased during a level turn, what action would be necessary to maintain altitude? The angle of attack
a. And angle of bank must be decreased
b. Must be increase or angle of bank decreased
c. Must be decreased or angle of bank increased
d. And angle of bank must be increased: c. Must be decreased or angle of bank
increased
Va = Vs sqrt n
L = V2 CL formula relations
6. 40. If a single rotor helicopter is in forward horizontal flight, the angle of
attack of the advancing blade is:
a. equal to the retreating blade
b. more than the retreating blade
C. less than the retreating blade
d. equal to the leading blade: C. less than the retreating blade
Sa advancing blade, higher lift, so need low AOA to balance
7. 42. It is an airfoil shaped attachment made of thin sheets of metal, plastic,
or composite material. This mount on the blade shanks and are primarily used
to increase the flow of cooling air to the engine nacelle.
Slinger ring
Blade cuffs
Townend Ring
Collector ring: Blade cuffs
8. Which force is not present during gliding? a. Thrust
b. Weight
c. Lift
d. Drag: A. THRUST
Lift is the force that opposes the weight of an aircraft and keeps it in the air.
9. Compared with an oblique shock wave at the same Mach number a normal
shock wave has a:
a. Higher expansion
b. Smaller compression
c. Smaller expansion
d. Higher compression: d. HIGHER COMPRESSION
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Kaya malaki pagbaba sa Mach number Compared to an oblique shock wave at the
same Mach number, a normal shock wave has a higher compression, which means
the flow is compressed more abruptly and the change in pressure and temperature
is greater.
10. An aerodynamic effect whereby the nose of an aircraft tends to pitch
downward as the airflow around the wing reaches supersonic speeds. CP
moves aft at high speed.: Mach tuck
11. It refers to the varying of wing chord using a uniform airfoil section
a. Airfoil Tapering
b. Planform Tapering
c. Section Tapering
d. Thickness Taperring: B. Planform tapering
12. On what instance does negative pressure coefficient occurs?
a. When local velocity is higher than freestream velocity
b. When the dynamic pressure is twice the pressure difference.
c. When the freestream velocity is higher than local velocity
d. When the local pressure is greater than freestream pressure.: A. When local
V is higher
13. The minimum speed at which intentional engine failures are to be performed.: Safe single-engine speed (Vsse)
14. Higher induced angle of attack can be obtained by using
a. lower taper ratio
b. larger wing area
c. higher wing aspect ratio
d. lower wing aspect ratio: D. Lower AR
Refer to CL vs AR graph
CL vs AOA – AR
15. When an airplane is at constant altitude bank, the stall speed will
a. remain the same as level flight condition.
b. increase as the square of the load factor
c. increase as the square root of the angle of bank
d. decrease as the square root of the load factor: C. Va or Vs turn = Vs sqrt n
16. In what flight condition are torque effects more pronounced in a single-engine airplane?
a. Low airspeed, high power, high angle of attack.
b. Low airspeed, low power, low angle of attack.
c. High airspeed, high power, high angle of attack.
d. High airspeed, low power, high angle of attack.: A. Low airspeed, high power,
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high angle of attack. Propeller is not generating as much thrust at low airspeed, so
the torque effect is more noticeable. The high power also contributes to the torque
effect, as the propeller is spinning faster and creating more torque. The high angle
of attack further exacerbates the torque effect, as the downwash from the wing is
pushing the propeller out of alignment with the engine.
17. When a blade flaps up, its CG will shift closer to the hub giving the blade
a tendency to?
a. speed up
b. slow down
c. stop
d. has no effect: A. SPEED UP
Moment = FD When a blade flaps up, its CG will shift closer to the hub and will speed
up. This is because the blade is now rotating in a smaller circle, so it needs to move
faster to maintain the same angular momentum.
18. For the maneuvering performance of airplanes, it is advantageous to have
the smallest r and the smallest w obtainable by
a. Have the highest load factor and the lowest possible velocity
b. Have the lowest load factor and the highest possible velocity
c. Have the highest load factor and the highest possible velocity
d. Have the lowest load factor and the lowest possible velocity: a. Have the
highest load factor and the lowest possible velocity
R = V2/g dqrt n2 -1
19. In steady symmetrical flight conditions, it is also called as the vertical flight
speed component
a. Rate of Descent
b. Rate of Climb
c. Rate of Ascent
d. Rate of Dive: A. Rate of Descent
L up = W down so bawal mag add ng Lift up, pwede lang down
20. Which maximum range factor decreases as weight decreases?
a. Stalling speed
b. altitude
C. airspeed d. angle of attack: C. Airspeed Low
W = low L = low V
21. If airspeed is increased during a level turn, what action would be necessary
to maintain altitude? The angle of attack
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a. and angle of bank must be decreased
b. must be increased or angle of bank decreased
c. must be decreased or angle of bank increased
d. and angle of bank must be increased: c. must be decreased or angle of bank
increased
balance n = L / W
22. To obtain the Smallest R and Fastest w:
n and V ___: n be as High as possible
V be as Low as possible
23. To increase the rate of turn and at the same time decrease the radius, a
pilot should
a. maintain the bank and decrease airspeed
b. increase the bank and increase airspeed
c. increase the bank and decrease airspeed
d. maintain the bank and increase airspeed: c. increase the bank and decrease
airspeed
24. This principle supports that the pressure on the surface depends on the
angle of deflection and upstream conditions.
A, First Order Theory
B. Second Order Theory
C. First Order Approximation
D. Second Order Approximation: C. First Order Approximation
25. The aircraft is said to be trimmed if?
a. The moment of aerodynamic center is zero
b. The rotation at the center of pressure is zero
c. The rotation at the center of gravity is zero
d. The rotation at the geometric center is zero: c. The rotation at the center of
gravity is zero.
An aircraft is said to be trimmed if it is flying in a stable and equilibrium condition.
26. When the angle of attack of a symmetrical airfoil is increased, the center
of pressure will:
A. Have very limited movement
B. Move aft along the airfoil surface
C. Remain unaffected
D. Move forward to the leading edge: C. Unaffected
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27. If airspeed is increased during a level turn, what action would be necessary
to maintain altitude? The angle of attack
a. and angle of bank must be decreased b. must be increased or angle of bank
decreased
c. must be decreased or angle of bank increased
d. and angle of bank must be increased: c. must be decreased or angle of bank
increased
28. Airplane wing loading during a level coordinated turn in smooth air depends upon the
a. radius of turn
b. rate of turn
c. angle of bank
d. true airspeed: C. angle of bank
L = S (else is constant)
n = L/(W/S)
29. One of the main functions of flaps during the approach and landing is to
a. decrease the angle of descent without increasing the airspeed
b. provide the same amount of lift at a slower airspeed
c. decrease lift, thus enabling a steeper than normal approach to be made
d. provide a substantial increase in drag to aid in landing.: B. provide the same
amount of lift at a slower airspeed.
By extending the flaps, the wing area and camber are increased, which generates
more lift at a lower airspeed.
30. What is the purpose of helical twist?
*
A reduction in blade angle towards the propeller tip to maintain best
thrust/torque ratio
An increase in blade angle towards the propeller tip to maintain best
thrust/torque ratio
A reduction in blade angle towards the propeller tip to maintain 16° AoA for
the entire blade length
An increase in blade angle towards the propeller tip to 16° AoA for the entire
blade length: A reduction in blade angle towards the propeller tip to maintain 16°
AoA for the entire blade length
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Low pitch sa tip, kasi high V na dito
31. What is used to correct any tendency of the aircraft to move towards an
undesirable flight altitude?
*
Trim tabs
Spring tabs
Slats
Balance tabs: “Trim” tabs
32. What must a pilot do to maintain a constant indicated airspeed (IAS) during
a climb?
A. Increase true airspeed (TAS) as altitude increases
B. Decease true airspeed (TAS) as altitude increases
C. Keep true airspeed (TAS) constant as altitude increases
D. Keep ground speed (GAS) constant as altitude increases: Increase true
airspeed (TAS) as altitude increases
during “climb”
33. This type of airfoil cross-sectional shape is considered to be the optimum
practical choice because it gives the least drag per unit stress.
*
Double Wedge
Biconvex
Diamond
Flat Plate: Biconvex
“least drag” – optimum choice
34. It shows the various combinations of horizontal and vertical speeds that
supply the required energy to keep the rotor turning at a constant rpm.
*
Autorotational Performance Chart
Hovering Performance Chart
Climb Performance Chart
H/V Diagram: Autorotational Performance Chart
35. In a fixed propeller, what happens to the angle of
attack of the blade if forward speed increases?
a. Goes to zero
b. Increases
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c. Decreases
d. Remains fixed: c. Decreases
Draw rpm, TAS triangle
36. Phugoid motion occurs at nearly constant __ with varying speeds.: AOA
37. Prevent an increase of the boundary layer at the wing tips of swept wings-
: Wing fence
38. What remains if the equipped empty weight of the
aircraft is subtracted from its zero fuel weight?
a. Payload
b. Ramp weight
c. Cargo
d. Gross Weight: a. Payload
39. An increase in which of the following will result in an increase in air
viscosity?
Pressure
Density
Temperature
Weight: Temperature
See formula to get viscosity in certain temperature
40. The true airspeed (TAS) is _____. 2pt
A. higher than the speed of the undisturbed airstream about the aeroplane.
B. equal to the IAS, multiplied by the air density at sea level
C. lower than the speed of the undisturbed airstream about the aeroplane
D. lower than the indicated airspeed (IAS) at ISA conditions and altitudes
below sea level: D. lower than the indicated airspeed (IAS) at ISA conditions and
altitudes below sea level
At high alt = High tas = low IAS
Sea level = TAS = IAS
Lower SL = low TAS = high IAS (kasi compact density here)
41. Regarding curved deflecting angles, what happens to the vertical component of force as the angle of deflection increases?
Assuming that all the other parameters remain constant. 2pt
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A. Increases
B. Decreases
C. No relationship
D. Remains the same: A. Increases
Fv = pav2 sin theta
42. Where on the surface of a typical aerofoil will flow separation normally start
at high angles of attack? 2pt
upper side leading edge
lower side trailing edge
lower side leading edge
upper side trailing edge: upper side trailing edge
43. NACA 4412 was used in the construction of the airfoil. Determine the chord
(in) if the camber equals 9.12 cm. 2pt
22.8
29.92
89.76
228: 89.76 inches di cm
44. An elliptical planform wing has a span of 12 m and a chord of 2 m. What is
the induced drag coefficient when the lift coefficient is 0.8? 2pt
0.034
0.43
0.068
0.86: Right Answer: A
0.034
45. Two identical aeroplanes A and B are flying horizontal steady turns. Further data are: Condition A W= 1500 kg Bank= 20 deg TAS= 130 kt Condition B
W= 1500 kg Bank= 20 deg TAS= 200 kt Which of the following statements is
correct? 2pt
A. The load factor for A is larger than the load factor for
B. The turn radius A is larger than the turn radius
C. The lift coefficient A is smaller than the lift coefficient
D. The rate of turn A is larger than the rate of Turn: Right Answer: D
D. The rate of turn A is larger than the rate of Turn
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46. How does the exterior view of an aircraft change, when the trim is used
during a speed decrease? 2pt
A. Elevator deflected downwards by means of a trimmable horizontal stabilizer
B. Nothing changes in exterior view
C. The elevator is deflected further downwards by means of an upwards
deflected trimtab
D. The elevator is deflected upwards by means of a downwards deflected
trimtab: D. The elevator is deflected upwards by means of a downwards deflected
trimtab
Method 1
“Trim” so need level flight
L = down V, up CL
up CL – El up, trim down
—
down V = elevator up = trim down
Speed will decrease in a nose-up attitude.High CL = 1/V low
47. VA is 2pt
A. The maximum speed at which rolls are allowed.
B. The speed that should not be exceeded in the climb.
C. The maximum speed at which maximum elevator deflection up is allowed.
D. The speed at which a heavy transport aircraft should fly in turbulence.: Right
Answer: C
C. The maximum speed at which maximum elevator deflection up is allowed.
48. Consider a rocket burning hydrogen and oxygen; the combustion chamber
pressure and temperature are 25 atm and 3,517 Kelvin, respectively. The area
of the rocket nozzle throat is 0.1 square meters.
The area of the exit is designed so that the exit pressure exactly equals
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ambient pressure at a standard altitude of 30 km. For the gas mixture assume
that k = 1.22 and the molecular weight M = 16. At a standard altitude of 30 km,
calculate exit Mach number. 2pt: 5.21
49. To be able to predict compressibility effects, you have to determine the 2pt
Mach Number
EAS
TAS
IAS: Right Answer: A
Mach Number
Compressibility effects become significant when the Mach number approaches or
exceeds 1.
50. Consider an oblique shock wave with ² = 35 deg and pressure ratio of
P2/P1=3. What is the upstream mach number? 2pt: 2.87
51. Effect of high density altitude to IAS and TAS: Indicated airspeed (IAS)
remains the same, the true airspeed (TAS) increases.
An increase in density altitude results in the following: Increased takeoff distance.
52. Which among the statements about Density Altitude is incorrect?
(2Pt)
A. Density altitude is found by correcting pressure altitude for temperature
and humidity deviations from the standard atmosphere
B. A high density altitude requires a higher true airspeed for takeoff and
landing and will therefore increase takeoff and landing distances
C. A high density altitude will decrease the power produced by an engine
because less oxygen is available for combustion
D. None, all statements above are correct: D. None, all statements above are
correct
53. Shock stall is: Separation of the boundary layer behind the shock wave.
54. When the Mach number is slowly increased in straight and level
flight the first shockwaves will occur (2Pt)
A. on the underside of the wing.
B. at the wing root segment, upperside.
C. somewhere on the fin.
D. somewhere on the hoizontal tail.: B. at the wing root segment, upperside.
55. If a symmetrical aerofoil is accelerated from subsonic to
supersonic speed the centre of lift will move _____. (2Pt)
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A. aft to the trailing edge
B. forward to the leading edge
C. aft to the mid chord
D. forward to the mid chord: C. aft to the mid chord
56. Fineness ratio is: fuselage length/max diameter
L/D
57. Upon which factor does wing loading during a level coordinated turn in
smooth air depend? (2Pt)
Angle of Attack
Rate of Turn
Angle of Bank
True Airspeed: Angle of Bank
“level” flight so n = 1
(1/cos theta) = L/W
58. The span-wise component of flow over the top surface of the wing
flows______. (2 Pt)
A. From wing-tip to root
B. Perpendicular to the wing upwards
C. From root to wing-tip
D. Along the free-stream direction: A. From wing-tip to root
Spanwise flow – vortex
If sinabing “spanwise flow” assume rectangular wing first, unless specified na swept
wing.
59. The quarter-chord moment coefficient for a cambered airfoil depends on
_________. (2Pt)
Chord Length
The shape of the airfoil
Angle of Attack
Center of pressure: B. The shape of the airfoil
Not chord length – Cma is always c/4.
The coefficient of moment about the quarter-chord is independent of angle of attack
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and chord length. It depends on the shape of the cambered airfoil (slope of the
camber line (dzdx)).
60. How to increase the critical angle of attack? (2Pt)
Reduce the camber
Increase the thickness
Increase the camber
Reduce the thickness: Reduce the camber
Draw CLa slope
61. At altitudes above sea-level, when flying at maximum velocity, the rate of
climb is (2Pt)
Beyond PE
Null
Equal to that at Max PE
Slightly below PE: Null
Aircraft is no longer generating any excess power.
The rate of climb at altitudes above sea level, when flying at maximum velocity, is
null, meaning it is zero. This is because at maximum velocity, the aircraft is using all
of its available power to overcome drag and maintain altitude, and there is no excess
power to be used for climbing.
62. Which kind of ‘tab’ is commonly used in case of manual reversion of fully
powered flight controls? (2Pt)
Spring tab
Servo tab
Balance tab
Anti-balance tab: Servo tab
The force applied by the pilot to the lever moves only the flap, and the flap also
moves the control surface until a balance is achieved. Even if external control locks
are placed on the control surface on the ground, the control commands in the cockpit
will be movable. This type of tab has been successfully used in old-style high-speed
jet transport aircraft, but their disadvantage is that they reduce the effectiveness of
the control surface at low IAS.
63. The tapering pipe is an example of __________. (2Pt)
Unsteady uniform flow
Unsteady non-uniform flow
Steady uniform flow
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Steady non-uniform flow: Steady non-uniform flow
Non uniform – condition changes – taper
Tapering lang di converging
Conditions change from point to point in the stream but do not change with time. An
example is flow in a tapering pipe with constant velocity at the inlet – velocity will
change as you move along the length of the pipe toward the exit.
64. Relative wind is defined as: (2 Pt)
A. The direction of the wind in relation to the chord line
B. The direction of the wind in relation to lift
C. The direction of the wind in relation to the airfoil
D. The direction of the wind in relation to the camber: C. The direction of the wind
in relation to the airfoil
The direction of the wind in relation to the AIRFOIL not chord line.
65. What is the expected duration of an individual microburst? (2Pt)
For as long as 1 hour
One microburst may continue for as long as 2 to 4 hours
Two minutes with maximum winds lasting approximately 1 minute
Seldom longer than 15 minutes from the time the burst strikes the ground
until dissipation: Seldom longer than 15 minutes from the time the burst strikes
the ground until dissipation
66. Why must the angle of attack be increased during a turn to maintain
altitude? (2 Pt)
A. Compensate for increase in drag
B. Compensate for loss of vertical component of lift
C. To prevent aircraft stall and increase lift
D. Increase the horizontal component of lift equal to the vertical component: B.
Compensate for loss of vertical component of lift
67. When you lower your flaps, stall speed _________. (2Pt)
decrease then increases
decrease
the same since
increase: decrease
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With flaps, you can fly at low speed
68. At zero angle of attack, the pressure along the upper surface of a symmetrical section would be
A. Greater than atmospheric pressure.
C. Less than atmospheric pressure.
B. Equal to atmospheric pressure .
D. Non existent: c. less than
69. What effect does an increase in airspeed have on a coordinated turn while
maintaining a
constant angle of bank and altitude?: B. rate of turn will decrease, no change in
load factor.
70. What effect does an increase in airspeed have on a coordinated turn while
maintaining a constant angle of bank and altitude?
The rate of turn will ___ and the load factor is ___: The rate of turn will decrease
resulting in no changes in load factor
W = V/R to get n = c since theta = c
71. A highspeed aircraft has an upside-down airfoil on the root of its wing.
What does it compensate for?
Increased drag
Loss of lift: Increased drag
Not loss of lift – may negative lift (draw airfoil)
72. Under what condition is pressure altitude and density altitude the same
value?
A. When indicated and pressure altitude are the same value in the altimeter.
B. At standard temperature.: At standard temperature.
Density altitude is pressure altitude corrected for temperature (and humidity).
Same temp at – P alt and rho alt formula.
Density altitude is the pressure altitude corrected for non-standard temperature and
pressure, it considers the air density, which is affected by temperature, pressure,
and humidity.
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73. As a result of gyroscopic precession, it can be said that any: yawing around
the normal axis results in a pitching moment.
74. The following are advantages of pusher type propellers except:
A. More advantages to seaplanes
B. Lesser Possibility to experience FOD damage to propeller: B. Lesser Possibility to experience FOD damage to propeller
Raymer:
Pusher propeller is more likely to be damaged by FOD thrown by the WHEELS.
75. Flux across a given surface is defined as:
A. Net rate of outflow
B. mass of fluid
C. Rate of volume flow: C. Rate of volume flow
Flux of a quantity is the rate at which it is transported across a surface.
76. Best angle-of-climb speed with one engine inoperative: VXSE
77. The bow wave will appear first at:
A M= Mcrit
B M= 0.6
C M= 1.3
D M= 1.0: D M= 1.0
78. A bow wave is: A shockwave that forms immediately ahead of an aircraft at M=
or > 1
Starts to appear at M = 1
79. In propeller, the asymmetric thrust effect is mainly induced by:
A high angles of attack.
B high speed.
C large angles of yaw.
D large angles of climb: A. high angles of attack.
At low speed,
down-going blade AOA > Up-going blade
Faster too.
Kaya More thrust on right part ng prop = yaw left
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80. increase drag = __ glide angle: increase
81. When the blades of a propeller are in the feathered
position:
A the propeller produces an optimal windmilling RPM.
B the windmilling RPM is the maximum.
C the RPM is then just sufficient to lubricate the engine.
D the drag of the propeller is then minimal.: D the drag of the propeller is then
minimal.
82. Propeller efficiency may be defined as the ratio between:
A usable (power available) power of the propeller and shaft
power.
B the thrust and the maximum thrust.
C the usable (power available) power and the maximum power.
D the thermal power of fuel-flow and shaft power.: A usable (power available)
power of the propeller and shaft
power.
83. Highest stall speed – (forward or aft) cg loading: Forward
Wing need more lift
L up = V up
84. Which forces produce the necessary normal acceleration to make an
aircraft turn?
A) The vertical component of lift.
B) Centrifugal force.
C) The horizontal component of weight.
D) The horizontal component of lift.: D) The horizontal component of lift.
85. A swept wing aircraft stalls and the wake contacts the horizontal tail. What
would
be the stall behaviour?
a. Nose down.
b. Nose up and/or elevator ineffectiveness.
c. Tendency to increase speed after stall.
d. Nose up.: b. Nose up and/or elevator ineffectiveness.
swept wing is forward-ing cp – FOR TIP STALL
86. What is the effect of a decreasing aeroplane weight on
Mcrit at n=1, when flying at constant IAS ? The value of
Mcrit:
A is independent of the angle of attack.
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B decreases.
C increases.
D remains constant.: C increases.
1pn (1) = L/ W low
Need low din Lift to keep level flight = AOA down
= High Mcrit
Concept: Need higher Mach to fly heavy ACs
87. An airplane said to be inherently stable will
a. Be difficult to stall
b. Not spin
c. Requires less effort to control
d. Have the easier tendency to pitch up or down: c. Requires less effort to control
A stable airplane is easy to fly. require less effort to control .
88. The angle of incidence is set at what angle?
a. Angle of attack at Cl˜•“
b. Angle of attack at (L/D)˜•“
c. Afa
d. Fafa: b. Angle of attack at (L/D)˜•“
89. When is the blade angle and angle of attack equal in a propeller blade?
a. When the plane is idle.
b. During take off.
c. During cruising.
d. When the engine power is off.: a. When the plane is idle.
Equal hindi zero ( 0 at power off)
90. When are outboard aileron (if present) de-activated?
a. Landing gear retracted
b. Landing gear extended
c. Flaps retracted or speed above a certain value
d. Flaps extended or speed below a certain value: c. Flaps retracted or speed
above a certain value
BOTH Aileron & flaps – not used
91. Compared with flap up configuration, the maximum angle of attack for
flaps down configuration is
a. Larger
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b. Smaller
c. Unchanged
d. Smaller of larger depends on flap deflection: b. Smaller
Draw CLa graph
92. What can happen to the aeroplane flying at a speed exceeding the V•?
a. It will collapse if a turn is made
b. It may break the elevator if fully deflected
c. It may cause permanent damage because of the too large dynamic pressure
d. It may suffer permanent deformation if the elevator is fully deflected upwards: d. It may suffer permanent deformation if the elevator is fully deflected
upwards
Oxford
93. What wing shape of wing characteristics is the least sensitive to turbulence?
a. Straight wings
b. Swept wings
c. Winglets
d. Wing dihedral: b. Swept wings
Delay shockwave formation
More efficient at generating lift at higher speeds
by reduces the amount of induced drag over the wing.
94. An aeroplane with the CG location behind the center of pressure of the
wing can only maintain a straight and level flight when the horizontal tail
loading is:
a. Upwards
b. Downwards
c. Zero
d. Upwards or downwards depending on elevator deflection: a. Upwards
95. Laminar flow is more likely to occur at:
a. High temperatures
b. High velocities
c. Low velocities
d. Low viscosities: c. Low velocities
Laminar flow is observed in high viscous fluids at low velocity.
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96. Flow separation at the
smallest angle of attack: shock stall
97. 6. What limits the high airspeed potential of a
helicopter?
a. harmonic resonance
b. Rotor RPM limitations
C.
d.
induced drag
retreating blade stall: retreating blade stall
98. Which of the following is true about boundary layer?
a. turbulent boundary layer is thinner
b. turbulent will separate more quickly than laminar
c. turbulent has more kinetic energy than laminar: c. turbulent has more kinetic
energy than laminar
clue: laging HIGHER sa turbulent
99. It is the mass of helicopter divided by area of rotor blades.
a. solidity c. blade loading
b. wing loading d. disc loading: d. disc loading
100. The boundary layer of the wing is caused by?
a. layer of the wing in which stream velocity is lower than free stream velocity,
due to friction
b. Normal Shockwave
c. turbulent stream
d. difference in air viscosity: a. “layer due to friction” – boundary layer
lower than V stream which is 0
101. What must you do to remain in formation as your aircraft takes on fuel
(increasing weight) from the tanker that is maintaining a
constant altitude and true airspeed?
A. Maintain a constant AOA and TAS
B. Decrease AOA and increase TAS
C. Increase AOA and maintain constant TAS
D. Increase AOA and TAS: d. Increase AOA and TAS
102. For a given altitude, what are the properties of the input provided by the
static pressure port in the pitot-static system?
A. The static pressure value will vary with changes in aircraft true airspeed
(TAS)
B. The static pressure value will vary with changes in aircraft angle of attack
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(AOA)
C. The static pressure value will vary with changes in aircraft weight
D. The static pressure value will vary with changes in atmospheric ambient
static pressure
and altitude: A. The static pressure value will vary with changes in aircraft true
airspeed (TAS)
103. What produces the most lift at low speeds?
(a) High camber (c) low aspect ratio
(b) Low camber (d) high aspect ratio: d. high AR
Cl a graph
104. Atmosphere is made of _________ of Argon.
a. 20.94 percent b. 78.08 percent
c. 0.001 percent d. 0.94 percent: d. 0.94
105. The propeller blade angle of
attack on a fixed pitch propeller
is increased when :
a. velocity and RPM decrease
o. RPM increases and forwara
velocity decreases
c. velocity and RPM increase
d. forward velocity increases and
RPM decreasing: B.. RPM increases and forward velocity decreases
106. In a twin-engined jet powered
aeroplane (engines mounted below
the low wings) the thrust is suddenly
increased. Which elevator deflection
will be required to maintain the
pitching moment zero ?
a. No elevator movement will required
because the thrust line of the engines
remains unchanged.
b. It depends on the position of the
center of gravity
c. Down
d. Up.: C. Down
Up Thrust = Up lift need nose down
107. The turn indicator shows a right turn.
The slip indicator is left of neutral. To
coordinate the turn:
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a. less right bank is required.
b. a higher turn rate is required.
c. more right bank is required
d. more right rudder is required: c. more right bank is required
108. Which statement is correct for a side
slip condition at constant speed and
side slip angle, where the geometric
dihedral of an aeroplane is increased ?
a. the required lateral control force
increases
b. the required lateral control force
decreases.: A. Increase
109. Which of the following wing planforms
gives the highest local profile lift
coefficient at the wingroot?
a. Rectangular.
b. Elliptical.
C. Tapered.
d. Positive angle of sweep.: A. Rectangle
110. Vortex generators on the upper side
of the wing:
a. increase critical Mach Number
b. decrease critical Mach Number
c, decrease wave drag: C. Decreases wave drag
111. In supersonic flight, all disturbances
produced by an aeroplane are:
a. in front of the aeroplane
b. very weak and negligible
c. in between a conical area,
depending on the Mach Number.
d. outside the conical area depending
on the Mach Number: C. In conical area
112. Changes in magnitude of total rotor thrust of the
main rotor during cruise are achieved by
a. Combining rotor speed change and blade pitch angle
b. Altering the pitch of the main rotor blades
collectively while the rotor speed is kept constant
c. Varying the speed of the main rotor, while the pitch
of the blade is constant
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d. Changing the speed of the air velocity around the
blade: b. Altering the pitch of the main rotor blades
collectively while the rotor speed is kept constant
113. What equation is obtained when Mach number is equated to zero in
area-velocity relation?
a. Momentum equation
b. Continuity equation
c. Energy equation
d. Bernoulli’s equation: continuity
114. 6.
In single-engine helicopters, if so equipped, the throttle control is
1. a twist grip mounted on the collective control
a lever mechanism in fully governed systems
typically a twist grip mounted on the collective control, but it can also be a
lever mechanism in
fully governed systems
D. fully typically governed a twist grip systems mounted
on the cyclic control, but it can also be a lever mechanism in: c. twist grip, and
lever
115. changes in AOI equally and in the same direction on all rotor blades
simultaneously. this changes AOA, which changes coefficient of lift (CL) and
affects overall lift of rotor disk: collective feathering
SAME AOA
116. changes in blade’s angle of incidence differentially around the rotor disk
and creates differential lift. Basically, the AOA of each blades changes based
on where it is on the tip-path plane. Used to control attitude of rotor disk.: cyclic
feathering
DIF. AOI
117. Because a shock wave does no work, and there is no heat addition, the
total enthalpy and the total temperature are constant. But because the flow
is non-isentropic, the total pressure downstream of the shock is always less
than the total pressure upstream of the shock. There is a loss of total pressure
associated with a shock wave. The ratio of the total pressure is shown on the
slide. Because total pressure changes across the shock, we can not use the
usual (incompressible) form of Bernoulli’s equation across the shock.: true
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Po changes, kasi with loss of total P
non isentropic
118. 21. With zero wind, the angle of attack for minimum drag for an airplane
is that:
A. the total drag equals one-third of induced drag
B. the total drag is equals to twice the induced drag
C. the total drag equals four times the induced drag
D thetotal drag is one-half the induced drag: b. CDO = CDI
D = 2cdi
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1. density decreases, true speed of aircraft ___: increases
As air density decreases, the true airspeed of an aircraft increases due to the
reduced AIR RESISTANCE.
The aircraft needs to move faster to generate the same amount of lift. This relationship is why aircraft fly faster at higher altitudes, where the air is less dense.
2. 8. 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.
C. High temperature with high humidity.
d.Low temperature with high humidity.:
C. High temperature with high humidity.
True airspeed (TAS) represents the true speed of an airplane through the air. As air
temperature and humidity increase, the density of the air decreases. As air density
decreases, true airspeed increases. Therefore, high temperature with high humidity
will cause an aircraft’s landing speed to be greatest.
3. 18. Frost covering the upper surface of an airplane wing will usually cause
a. The airplane to stall at an angle of attack that is higher than normal
b. The airplane to stall at an angle of attack that is lower than normal
c. Drag factors so large that sufficient speed cannot be obtained for take off
d. Coefficient of drag to increase abruptly:
b. The airplane to stall at an angle of
attack that is lower than normal
Magsstall agad
See CL a curve
4. 24. Recovery from a stall in any airplane becomes more difficult when its
Center of gravity moves aft
Center of gravity moves forward
Elevator trim is adjusted nose down Rudder travel is improperly adjusted: –
Center of gravity moves aft
If CG at aft (tail heavy) – tail force cant do downwards
Higher moment (high distance of CP and CG) = mas mahirap macontrol
5. 26. If airspeed is increased during a level turn, what action would be necessary to maintain altitude? The angle of attack
a. And angle of bank must be decreased
b. Must be increase or angle of bank decreased
c. Must be decreased or angle of bank increased
d. And angle of bank must be increased:
c. Must be decreased or angle of bank
increased
Va = Vs sqrt n
L = V2 CL formula relations
6. 40. If a single rotor helicopter is in forward horizontal flight, the angle of
attack of the advancing blade is:
a. equal to the retreating blade
b. more than the retreating blade
C. less than the retreating blade
d. equal to the leading blade:
C. less than the retreating blade
Sa advancing blade, higher lift, so need low AOA to balance
7. 42. It is an airfoil shaped attachment made of thin sheets of metal, plastic,
or composite material. This mount on the blade shanks and are primarily used
to increase the flow of cooling air to the engine nacelle.
Slinger ring
Blade cuffs
Townend Ring
Collector ring: Blade cuffs
8. Which force is not present during gliding? a. Thrust
b. Weight
c. Lift
d. Drag:
A. THRUST
Lift is the force that opposes the weight of an aircraft and keeps it in the air.
9. Compared with an oblique shock wave at the same Mach number a normal
shock wave has a:
a. Higher expansion
b. Smaller compression
c. Smaller expansion
d. Higher compression:
d. HIGHER COMPRESSION
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Kaya malaki pagbaba sa Mach number Compared to an oblique shock wave at the
same Mach number, a normal shock wave has a higher compression, which means
the flow is compressed more abruptly and the change in pressure and temperature
is greater.
10. An aerodynamic effect whereby the nose of an aircraft tends to pitch
downward as the airflow around the wing reaches supersonic speeds. CP
moves aft at high speed.: Mach tuck
11. It refers to the varying of wing chord using a uniform airfoil section
a. Airfoil Tapering
b. Planform Tapering
c. Section Tapering
d. Thickness Taperring:
B. Planform tapering
12. On what instance does negative pressure coefficient occurs?
a. When local velocity is higher than freestream velocity
b. When the dynamic pressure is twice the pressure difference.
c. When the freestream velocity is higher than local velocity
d. When the local pressure is greater than freestream pressure.:
A. When local V is higher
13. The minimum speed at which intentional engine failures are to be performed.: Safe single-engine speed (Vsse)
14. Higher induced angle of attack can be obtained by using
a. lower taper ratio
b. larger wing area
c. higher wing aspect ratio
d. lower wing aspect ratio:
D. Lower AR
Refer to CL vs AR graph
CL vs AOA – AR
15. When an airplane is at constant altitude bank, the stall speed will
a. remain the same as level flight condition.
b. increase as the square of the load factor
c. increase as the square root of the angle of bank
d. decrease as the square root of the load factor:
C. Va or Vs turn = Vs sqrt n
16. In what flight condition are torque effects more pronounced in a single-engine airplane?
a. Low airspeed, high power, high angle of attack.
b. Low airspeed, low power, low angle of attack.
c. High airspeed, high power, high angle of attack.
d. High airspeed, low power, high angle of attack.:
A. Low airspeed, high power,
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high angle of attack. Propeller is not generating as much thrust at low airspeed, so
the torque effect is more noticeable. The high power also contributes to the torque
effect, as the propeller is spinning faster and creating more torque. The high angle
of attack further exacerbates the torque effect, as the downwash from the wing is
pushing the propeller out of alignment with the engine.
17. When a blade flaps up, its CG will shift closer to the hub giving the blade
a tendency to?
a. speed up
b. slow down
c. stop
d. has no effect:
A. SPEED UP
Moment = FD When a blade flaps up, its CG will shift closer to the hub and will speed
up. This is because the blade is now rotating in a smaller circle, so it needs to move
faster to maintain the same angular momentum.
18. For the maneuvering performance of airplanes, it is advantageous to have
the smallest r and the smallest w obtainable by
a. Have the highest load factor and the lowest possible velocity
b. Have the lowest load factor and the highest possible velocity
c. Have the highest load factor and the highest possible velocity
d. Have the lowest load factor and the lowest possible velocity:
a. Have the highest load factor and the lowest possible velocity
R = V2/g dqrt n2 -1
19. In steady symmetrical flight conditions, it is also called as the vertical flight
speed component
a. Rate of Descent
b. Rate of Climb
c. Rate of Ascent
d. Rate of Dive:
A. Rate of Descent
L up = W down so bawal mag add ng Lift up, pwede lang down
20. Which maximum range factor decreases as weight decreases?
a. Stalling speed
b. altitude
C. airspeed d. angle of attack:
C. Airspeed Low
W = low L = low V
21. If airspeed is increased during a level turn, what action would be necessary
to maintain altitude? The angle of attack
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a. and angle of bank must be decreased
b. must be increased or angle of bank decreased
c. must be decreased or angle of bank increased
d. and angle of bank must be increased: c. must be decreased or angle of bank
increased
balance n = L / W
22. To obtain the Smallest R and Fastest w:
n and V ___: n be as High as possible
V be as Low as possible
23. To increase the rate of turn and at the same time decrease the radius, a
pilot should
a. maintain the bank and decrease airspeed
b. increase the bank and increase airspeed
c. increase the bank and decrease airspeed
d. maintain the bank and increase airspeed: c. increase the bank and decrease
airspeed
24. This principle supports that the pressure on the surface depends on the
angle of deflection and upstream conditions.
A, First Order Theory
B. Second Order Theory
C. First Order Approximation
D. Second Order Approximation: C. First Order Approximation
25. The aircraft is said to be trimmed if?
a. The moment of aerodynamic center is zero
b. The rotation at the center of pressure is zero
c. The rotation at the center of gravity is zero
d. The rotation at the geometric center is zero: c. The rotation at the center of
gravity is zero.
An aircraft is said to be trimmed if it is flying in a stable and equilibrium condition.
26. When the angle of attack of a symmetrical airfoil is increased, the center
of pressure will:
A. Have very limited movement
B. Move aft along the airfoil surface
C. Remain unaffected
D. Move forward to the leading edge: C. Unaffected
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27. If airspeed is increased during a level turn, what action would be necessary
to maintain altitude? The angle of attack
a. and angle of bank must be decreased b. must be increased or angle of bank
decreased
c. must be decreased or angle of bank increased
d. and angle of bank must be increased: c. must be decreased or angle of bank
increased
28. Airplane wing loading during a level coordinated turn in smooth air depends upon the
a. radius of turn
b. rate of turn
c. angle of bank
d. true airspeed: C. angle of bank
L = S (else is constant)
n = L/(W/S)
29. One of the main functions of flaps during the approach and landing is to
a. decrease the angle of descent without increasing the airspeed
b. provide the same amount of lift at a slower airspeed
c. decrease lift, thus enabling a steeper than normal approach to be made
d. provide a substantial increase in drag to aid in landing.: B. provide the same
amount of lift at a slower airspeed.
By extending the flaps, the wing area and camber are increased, which generates
more lift at a lower airspeed.
30. What is the purpose of helical twist?
*
A reduction in blade angle towards the propeller tip to maintain best
thrust/torque ratio
An increase in blade angle towards the propeller tip to maintain best
thrust/torque ratio
A reduction in blade angle towards the propeller tip to maintain 16° AoA for
the entire blade length
An increase in blade angle towards the propeller tip to 16° AoA for the entire
blade length: A reduction in blade angle towards the propeller tip to maintain 16°
AoA for the entire blade length
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Low pitch sa tip, kasi high V na dito
31. What is used to correct any tendency of the aircraft to move towards an
undesirable flight altitude?
*
Trim tabs
Spring tabs
Slats
Balance tabs: “Trim” tabs
32. What must a pilot do to maintain a constant indicated airspeed (IAS) during
a climb?
A. Increase true airspeed (TAS) as altitude increases
B. Decease true airspeed (TAS) as altitude increases
C. Keep true airspeed (TAS) constant as altitude increases
D. Keep ground speed (GAS) constant as altitude increases: Increase true
airspeed (TAS) as altitude increases
during “climb”
33. This type of airfoil cross-sectional shape is considered to be the optimum
practical choice because it gives the least drag per unit stress.
*
Double Wedge
Biconvex
Diamond
Flat Plate: Biconvex
“least drag” – optimum choice
34. It shows the various combinations of horizontal and vertical speeds that
supply the required energy to keep the rotor turning at a constant rpm.
*
Autorotational Performance Chart
Hovering Performance Chart
Climb Performance Chart
H/V Diagram: Autorotational Performance Chart
35. In a fixed propeller, what happens to the angle of
attack of the blade if forward speed increases?
a. Goes to zero
b. Increases
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c. Decreases
d. Remains fixed: c. Decreases
Draw rpm, TAS triangle
36. Phugoid motion occurs at nearly constant __ with varying speeds.: AOA
37. Prevent an increase of the boundary layer at the wing tips of swept wings-
: Wing fence
38. What remains if the equipped empty weight of the
aircraft is subtracted from its zero fuel weight?
a. Payload
b. Ramp weight
c. Cargo
d. Gross Weight: a. Payload
39. An increase in which of the following will result in an increase in air
viscosity?
Pressure
Density
Temperature
Weight: Temperature
See formula to get viscosity in certain temperature
40. The true airspeed (TAS) is _____. 2pt
A. higher than the speed of the undisturbed airstream about the aeroplane.
B. equal to the IAS, multiplied by the air density at sea level
C. lower than the speed of the undisturbed airstream about the aeroplane
D. lower than the indicated airspeed (IAS) at ISA conditions and altitudes
below sea level: D. lower than the indicated airspeed (IAS) at ISA conditions and
altitudes below sea level
At high alt = High tas = low IAS
Sea level = TAS = IAS
Lower SL = low TAS = high IAS (kasi compact density here)
41. Regarding curved deflecting angles, what happens to the vertical component of force as the angle of deflection increases?
Assuming that all the other parameters remain constant. 2pt
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A. Increases
B. Decreases
C. No relationship
D. Remains the same: A. Increases
Fv = pav2 sin theta
42. Where on the surface of a typical aerofoil will flow separation normally start
at high angles of attack? 2pt
upper side leading edge
lower side trailing edge
lower side leading edge
upper side trailing edge: upper side trailing edge
43. NACA 4412 was used in the construction of the airfoil. Determine the chord
(in) if the camber equals 9.12 cm. 2pt
22.8
29.92
89.76
228: 89.76 inches di cm
44. An elliptical planform wing has a span of 12 m and a chord of 2 m. What is
the induced drag coefficient when the lift coefficient is 0.8? 2pt
0.034
0.43
0.068
0.86: Right Answer: A
0.034
45. Two identical aeroplanes A and B are flying horizontal steady turns. Further data are: Condition A W= 1500 kg Bank= 20 deg TAS= 130 kt Condition B
W= 1500 kg Bank= 20 deg TAS= 200 kt Which of the following statements is
correct? 2pt
A. The load factor for A is larger than the load factor for
B. The turn radius A is larger than the turn radius
C. The lift coefficient A is smaller than the lift coefficient
D. The rate of turn A is larger than the rate of Turn: Right Answer: D
D. The rate of turn A is larger than the rate of Turn
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46. How does the exterior view of an aircraft change, when the trim is used
during a speed decrease? 2pt
A. Elevator deflected downwards by means of a trimmable horizontal stabilizer
B. Nothing changes in exterior view
C. The elevator is deflected further downwards by means of an upwards
deflected trimtab
D. The elevator is deflected upwards by means of a downwards deflected
trimtab: D. The elevator is deflected upwards by means of a downwards deflected
trimtab
Method 1
“Trim” so need level flight
L = down V, up CL
up CL – El up, trim down
—
down V = elevator up = trim down
Speed will decrease in a nose-up attitude.High CL = 1/V low
47. VA is 2pt
A. The maximum speed at which rolls are allowed.
B. The speed that should not be exceeded in the climb.
C. The maximum speed at which maximum elevator deflection up is allowed.
D. The speed at which a heavy transport aircraft should fly in turbulence.: Right
Answer: C
C. The maximum speed at which maximum elevator deflection up is allowed.
48. Consider a rocket burning hydrogen and oxygen; the combustion chamber
pressure and temperature are 25 atm and 3,517 Kelvin, respectively. The area
of the rocket nozzle throat is 0.1 square meters.
The area of the exit is designed so that the exit pressure exactly equals
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ambient pressure at a standard altitude of 30 km. For the gas mixture assume
that k = 1.22 and the molecular weight M = 16. At a standard altitude of 30 km,
calculate exit Mach number. 2pt: 5.21
49. To be able to predict compressibility effects, you have to determine the 2pt
Mach Number
EAS
TAS
IAS: Right Answer: A
Mach Number
Compressibility effects become significant when the Mach number approaches or
exceeds 1.
50. Consider an oblique shock wave with ² = 35 deg and pressure ratio of
P2/P1=3. What is the upstream mach number? 2pt: 2.87
51. Effect of high density altitude to IAS and TAS: Indicated airspeed (IAS)
remains the same, the true airspeed (TAS) increases.
An increase in density altitude results in the following: Increased takeoff distance.
52. Which among the statements about Density Altitude is incorrect?
(2Pt)
A. Density altitude is found by correcting pressure altitude for temperature
and humidity deviations from the standard atmosphere
B. A high density altitude requires a higher true airspeed for takeoff and
landing and will therefore increase takeoff and landing distances
C. A high density altitude will decrease the power produced by an engine
because less oxygen is available for combustion
D. None, all statements above are correct: D. None, all statements above are
correct
53. Shock stall is: Separation of the boundary layer behind the shock wave.
54. When the Mach number is slowly increased in straight and level
flight the first shockwaves will occur (2Pt)
A. on the underside of the wing.
B. at the wing root segment, upperside.
C. somewhere on the fin.
D. somewhere on the hoizontal tail.: B. at the wing root segment, upperside.
55. If a symmetrical aerofoil is accelerated from subsonic to
supersonic speed the centre of lift will move _____. (2Pt)
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A. aft to the trailing edge
B. forward to the leading edge
C. aft to the mid chord
D. forward to the mid chord: C. aft to the mid chord
56. Fineness ratio is: fuselage length/max diameter
L/D
57. Upon which factor does wing loading during a level coordinated turn in
smooth air depend? (2Pt)
Angle of Attack
Rate of Turn
Angle of Bank
True Airspeed: Angle of Bank
“level” flight so n = 1
(1/cos theta) = L/W
58. The span-wise component of flow over the top surface of the wing
flows______. (2 Pt)
A. From wing-tip to root
B. Perpendicular to the wing upwards
C. From root to wing-tip
D. Along the free-stream direction: A. From wing-tip to root
Spanwise flow – vortex
If sinabing “spanwise flow” assume rectangular wing first, unless specified na swept
wing.
59. The quarter-chord moment coefficient for a cambered airfoil depends on
_________. (2Pt)
Chord Length
The shape of the airfoil
Angle of Attack
Center of pressure: B. The shape of the airfoil
Not chord length – Cma is always c/4.
The coefficient of moment about the quarter-chord is independent of angle of attack
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and chord length. It depends on the shape of the cambered airfoil (slope of the
camber line (dzdx)).
60. How to increase the critical angle of attack? (2Pt)
Reduce the camber
Increase the thickness
Increase the camber
Reduce the thickness: Reduce the camber
Draw CLa slope
61. At altitudes above sea-level, when flying at maximum velocity, the rate of
climb is (2Pt)
Beyond PE
Null
Equal to that at Max PE
Slightly below PE: Null
Aircraft is no longer generating any excess power.
The rate of climb at altitudes above sea level, when flying at maximum velocity, is
null, meaning it is zero. This is because at maximum velocity, the aircraft is using all
of its available power to overcome drag and maintain altitude, and there is no excess
power to be used for climbing.
62. Which kind of ‘tab’ is commonly used in case of manual reversion of fully
powered flight controls? (2Pt)
Spring tab
Servo tab
Balance tab
Anti-balance tab: Servo tab
The force applied by the pilot to the lever moves only the flap, and the flap also
moves the control surface until a balance is achieved. Even if external control locks
are placed on the control surface on the ground, the control commands in the cockpit
will be movable. This type of tab has been successfully used in old-style high-speed
jet transport aircraft, but their disadvantage is that they reduce the effectiveness of
the control surface at low IAS.
63. The tapering pipe is an example of __________. (2Pt)
Unsteady uniform flow
Unsteady non-uniform flow
Steady uniform flow
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Steady non-uniform flow: Steady non-uniform flow
Non uniform – condition changes – taper
Tapering lang di converging
Conditions change from point to point in the stream but do not change with time. An
example is flow in a tapering pipe with constant velocity at the inlet – velocity will
change as you move along the length of the pipe toward the exit.
64. Relative wind is defined as: (2 Pt)
A. The direction of the wind in relation to the chord line
B. The direction of the wind in relation to lift
C. The direction of the wind in relation to the airfoil
D. The direction of the wind in relation to the camber: C. The direction of the wind
in relation to the airfoil
The direction of the wind in relation to the AIRFOIL not chord line.
65. What is the expected duration of an individual microburst? (2Pt)
For as long as 1 hour
One microburst may continue for as long as 2 to 4 hours
Two minutes with maximum winds lasting approximately 1 minute
Seldom longer than 15 minutes from the time the burst strikes the ground
until dissipation: Seldom longer than 15 minutes from the time the burst strikes
the ground until dissipation
66. Why must the angle of attack be increased during a turn to maintain
altitude? (2 Pt)
A. Compensate for increase in drag
B. Compensate for loss of vertical component of lift
C. To prevent aircraft stall and increase lift
D. Increase the horizontal component of lift equal to the vertical component: B.
Compensate for loss of vertical component of lift
67. When you lower your flaps, stall speed _________. (2Pt)
decrease then increases
decrease
the same since
increase: decrease
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With flaps, you can fly at low speed
68. At zero angle of attack, the pressure along the upper surface of a symmetrical section would be
A. Greater than atmospheric pressure.
C. Less than atmospheric pressure.
B. Equal to atmospheric pressure .
D. Non existent: c. less than
69. What effect does an increase in airspeed have on a coordinated turn while
maintaining a
constant angle of bank and altitude?: B. rate of turn will decrease, no change in
load factor.
70. What effect does an increase in airspeed have on a coordinated turn while
maintaining a constant angle of bank and altitude?
The rate of turn will ___ and the load factor is ___: The rate of turn will decrease
resulting in no changes in load factor
W = V/R to get n = c since theta = c
71. A highspeed aircraft has an upside-down airfoil on the root of its wing.
What does it compensate for?
Increased drag
Loss of lift: Increased drag
Not loss of lift – may negative lift (draw airfoil)
72. Under what condition is pressure altitude and density altitude the same
value?
A. When indicated and pressure altitude are the same value in the altimeter.
B. At standard temperature.: At standard temperature.
Density altitude is pressure altitude corrected for temperature (and humidity).
Same temp at – P alt and rho alt formula.
Density altitude is the pressure altitude corrected for non-standard temperature and
pressure, it considers the air density, which is affected by temperature, pressure,
and humidity.
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73. As a result of gyroscopic precession, it can be said that any: yawing around
the normal axis results in a pitching moment.
74. The following are advantages of pusher type propellers except:
A. More advantages to seaplanes
B. Lesser Possibility to experience FOD damage to propeller: B. Lesser Possibility to experience FOD damage to propeller
Raymer:
Pusher propeller is more likely to be damaged by FOD thrown by the WHEELS.
75. Flux across a given surface is defined as:
A. Net rate of outflow
B. mass of fluid
C. Rate of volume flow: C. Rate of volume flow
Flux of a quantity is the rate at which it is transported across a surface.
76. Best angle-of-climb speed with one engine inoperative: VXSE
77. The bow wave will appear first at:
A M= Mcrit
B M= 0.6
C M= 1.3
D M= 1.0: D M= 1.0
78. A bow wave is: A shockwave that forms immediately ahead of an aircraft at M=
or > 1
Starts to appear at M = 1
79. In propeller, the asymmetric thrust effect is mainly induced by:
A high angles of attack.
B high speed.
C large angles of yaw.
D large angles of climb: A. high angles of attack.
At low speed,
down-going blade AOA > Up-going blade
Faster too.
Kaya More thrust on right part ng prop = yaw left
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80. increase drag = __ glide angle: increase
81. When the blades of a propeller are in the feathered
position:
A the propeller produces an optimal windmilling RPM.
B the windmilling RPM is the maximum.
C the RPM is then just sufficient to lubricate the engine.
D the drag of the propeller is then minimal.: D the drag of the propeller is then
minimal.
82. Propeller efficiency may be defined as the ratio between:
A usable (power available) power of the propeller and shaft
power.
B the thrust and the maximum thrust.
C the usable (power available) power and the maximum power.
D the thermal power of fuel-flow and shaft power.: A usable (power available)
power of the propeller and shaft
power.
83. Highest stall speed – (forward or aft) cg loading: Forward
Wing need more lift
L up = V up
84. Which forces produce the necessary normal acceleration to make an
aircraft turn?
A) The vertical component of lift.
B) Centrifugal force.
C) The horizontal component of weight.
D) The horizontal component of lift.: D) The horizontal component of lift.
85. A swept wing aircraft stalls and the wake contacts the horizontal tail. What
would
be the stall behaviour?
a. Nose down.
b. Nose up and/or elevator ineffectiveness.
c. Tendency to increase speed after stall.
d. Nose up.: b. Nose up and/or elevator ineffectiveness.
swept wing is forward-ing cp – FOR TIP STALL
86. What is the effect of a decreasing aeroplane weight on
Mcrit at n=1, when flying at constant IAS ? The value of
Mcrit:
A is independent of the angle of attack.
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B decreases.
C increases.
D remains constant.: C increases.
1pn (1) = L/ W low
Need low din Lift to keep level flight = AOA down
= High Mcrit
Concept: Need higher Mach to fly heavy ACs
87. An airplane said to be inherently stable will
a. Be difficult to stall
b. Not spin
c. Requires less effort to control
d. Have the easier tendency to pitch up or down: c. Requires less effort to control
A stable airplane is easy to fly. require less effort to control .
88. The angle of incidence is set at what angle?
a. Angle of attack at Cl˜•“
b. Angle of attack at (L/D)˜•“
c. Afa
d. Fafa: b. Angle of attack at (L/D)˜•“
89. When is the blade angle and angle of attack equal in a propeller blade?
a. When the plane is idle.
b. During take off.
c. During cruising.
d. When the engine power is off.: a. When the plane is idle.
Equal hindi zero ( 0 at power off)
90. When are outboard aileron (if present) de-activated?
a. Landing gear retracted
b. Landing gear extended
c. Flaps retracted or speed above a certain value
d. Flaps extended or speed below a certain value: c. Flaps retracted or speed
above a certain value
BOTH Aileron & flaps – not used
91. Compared with flap up configuration, the maximum angle of attack for
flaps down configuration is
a. Larger
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b. Smaller
c. Unchanged
d. Smaller of larger depends on flap deflection: b. Smaller
Draw CLa graph
92. What can happen to the aeroplane flying at a speed exceeding the V•?
a. It will collapse if a turn is made
b. It may break the elevator if fully deflected
c. It may cause permanent damage because of the too large dynamic pressure
d. It may suffer permanent deformation if the elevator is fully deflected upwards: d. It may suffer permanent deformation if the elevator is fully deflected
upwards
Oxford
93. What wing shape of wing characteristics is the least sensitive to turbulence?
a. Straight wings
b. Swept wings
c. Winglets
d. Wing dihedral: b. Swept wings
Delay shockwave formation
More efficient at generating lift at higher speeds
by reduces the amount of induced drag over the wing.
94. An aeroplane with the CG location behind the center of pressure of the
wing can only maintain a straight and level flight when the horizontal tail
loading is:
a. Upwards
b. Downwards
c. Zero
d. Upwards or downwards depending on elevator deflection: a. Upwards
95. Laminar flow is more likely to occur at:
a. High temperatures
b. High velocities
c. Low velocities
d. Low viscosities: c. Low velocities
Laminar flow is observed in high viscous fluids at low velocity.
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96. Flow separation at the
smallest angle of attack: shock stall
97. 6. What limits the high airspeed potential of a
helicopter?
a. harmonic resonance
b. Rotor RPM limitations
C.
d.
induced drag
retreating blade stall: retreating blade stall
98. Which of the following is true about boundary layer?
a. turbulent boundary layer is thinner
b. turbulent will separate more quickly than laminar
c. turbulent has more kinetic energy than laminar: c. turbulent has more kinetic
energy than laminar
clue: laging HIGHER sa turbulent
99. It is the mass of helicopter divided by area of rotor blades.
a. solidity c. blade loading
b. wing loading d. disc loading: d. disc loading
100. The boundary layer of the wing is caused by?
a. layer of the wing in which stream velocity is lower than free stream velocity,
due to friction
b. Normal Shockwave
c. turbulent stream
d. difference in air viscosity: a. “layer due to friction” – boundary layer
lower than V stream which is 0
101. What must you do to remain in formation as your aircraft takes on fuel
(increasing weight) from the tanker that is maintaining a
constant altitude and true airspeed?
A. Maintain a constant AOA and TAS
B. Decrease AOA and increase TAS
C. Increase AOA and maintain constant TAS
D. Increase AOA and TAS: d. Increase AOA and TAS
102. For a given altitude, what are the properties of the input provided by the
static pressure port in the pitot-static system?
A. The static pressure value will vary with changes in aircraft true airspeed
(TAS)
B. The static pressure value will vary with changes in aircraft angle of attack
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(AOA)
C. The static pressure value will vary with changes in aircraft weight
D. The static pressure value will vary with changes in atmospheric ambient
static pressure
and altitude: A. The static pressure value will vary with changes in aircraft true
airspeed (TAS)
103. What produces the most lift at low speeds?
(a) High camber (c) low aspect ratio
(b) Low camber (d) high aspect ratio: d. high AR
Cl a graph
104. Atmosphere is made of _________ of Argon.
a. 20.94 percent b. 78.08 percent
c. 0.001 percent d. 0.94 percent: d. 0.94
105. The propeller blade angle of
attack on a fixed pitch propeller
is increased when :
a. velocity and RPM decrease
o. RPM increases and forwara
velocity decreases
c. velocity and RPM increase
d. forward velocity increases and
RPM decreasing: B.. RPM increases and forward velocity decreases
106. In a twin-engined jet powered
aeroplane (engines mounted below
the low wings) the thrust is suddenly
increased. Which elevator deflection
will be required to maintain the
pitching moment zero ?
a. No elevator movement will required
because the thrust line of the engines
remains unchanged.
b. It depends on the position of the
center of gravity
c. Down
d. Up.: C. Down
Up Thrust = Up lift need nose down
107. The turn indicator shows a right turn.
The slip indicator is left of neutral. To
coordinate the turn:
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a. less right bank is required.
b. a higher turn rate is required.
c. more right bank is required
d. more right rudder is required: c. more right bank is required
108. Which statement is correct for a side
slip condition at constant speed and
side slip angle, where the geometric
dihedral of an aeroplane is increased ?
a. the required lateral control force
increases
b. the required lateral control force
decreases.: A. Increase
109. Which of the following wing planforms
gives the highest local profile lift
coefficient at the wingroot?
a. Rectangular.
b. Elliptical.
C. Tapered.
d. Positive angle of sweep.: A. Rectangle
110. Vortex generators on the upper side
of the wing:
a. increase critical Mach Number
b. decrease critical Mach Number
c, decrease wave drag: C. Decreases wave drag
111. In supersonic flight, all disturbances
produced by an aeroplane are:
a. in front of the aeroplane
b. very weak and negligible
c. in between a conical area,
depending on the Mach Number.
d. outside the conical area depending
on the Mach Number: C. In conical area
112. Changes in magnitude of total rotor thrust of the
main rotor during cruise are achieved by
a. Combining rotor speed change and blade pitch angle
b. Altering the pitch of the main rotor blades
collectively while the rotor speed is kept constant
c. Varying the speed of the main rotor, while the pitch
of the blade is constant
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d. Changing the speed of the air velocity around the
blade: b. Altering the pitch of the main rotor blades
collectively while the rotor speed is kept constant
113. What equation is obtained when Mach number is equated to zero in
area-velocity relation?
a. Momentum equation
b. Continuity equation
c. Energy equation
d. Bernoulli’s equation: continuity
114. 6.
In single-engine helicopters, if so equipped, the throttle control is
1. a twist grip mounted on the collective control
a lever mechanism in fully governed systems
typically a twist grip mounted on the collective control, but it can also be a
lever mechanism in
fully governed systems
D. fully typically governed a twist grip systems mounted
on the cyclic control, but it can also be a lever mechanism in: c. twist grip, and
lever
115. changes in AOI equally and in the same direction on all rotor blades
simultaneously. this changes AOA, which changes coefficient of lift (CL) and
affects overall lift of rotor disk: collective feathering
SAME AOA
116. changes in blade’s angle of incidence differentially around the rotor disk
and creates differential lift. Basically, the AOA of each blades changes based
on where it is on the tip-path plane. Used to control attitude of rotor disk.: cyclic
feathering
DIF. AOI
117. Because a shock wave does no work, and there is no heat addition, the
total enthalpy and the total temperature are constant. But because the flow
is non-isentropic, the total pressure downstream of the shock is always less
than the total pressure upstream of the shock. There is a loss of total pressure
associated with a shock wave. The ratio of the total pressure is shown on the
slide. Because total pressure changes across the shock, we can not use the
usual (incompressible) form of Bernoulli’s equation across the shock.: true
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Po changes, kasi with loss of total P
non isentropic
118. 21. With zero wind, the angle of attack for minimum drag for an airplane
is that:
A. the total drag equals one-third of induced drag
B. the total drag is equals to twice the induced drag
C. the total drag equals four times the induced drag
D thetotal drag is one-half the induced drag: b. CDO = CDI
D = 2cdi
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