POF

Question 1

Which of the following reduces induced drag?

Flush Rivets

Fillets

Winglets

Streamlining

Answer 1

Winglets

Question 2

In flight, the increased airflow velocity over the wings upper surface causes a …………….
in static pressure and a ……………. in dynamic pressure.

Decrease, Increase

Increase, Decrease

Decrease, Decrease

Increase, Decrease

Answer 2

Decrease, Increase

Question 3

The aerodynamic force can be said to act through which point?

The centre of pressure

The centre of gravity

The centre of mass

The centre of the aeroplane

Answer 3

The centre of pressure

Question 4

Consider an aircraft flying straight and level. As speed decreases the span wise flow ………………., the steepness of the EAF …………… and the induced Drag ………….

Answer 4

Increases
Increases
Increases

Question 5

Flap selection at constant IAS whilst maintaining straight and level flight will increase the:

maximum lift coefficient (CL max) and the drag

stall speed

lift coefficient and the drag

lift and the drag

Answer 5

maximum lift coefficient (CL max) and the drag

Question 6

Which combination is likely to produce the strongest tip vortices

constant lift production, constant airspeed, high aspect ratio

low aspect ratio, low airspeed, high lift production

low lift production, low aspect ratio, high airspeed

high aspect ratio, low airspeed, high lift production

Answer 6

low aspect ratio, low airspeed, high lift production

Question 7

When an aeroplane is flying at an airspeed which is 1.9 times its basic stalling speed, the coefficient of lift as a percentage of the maximum lift coefficient (CLmax) would be:

28%

52%

73%

113%

Answer 7

28%

Question 8

Select the correct properties of a turbulent boundary layer

minimal drag

high energy

a few centimetres thick

shallow velocity gradient

Answer 8

a few centimetres thick

high energy

Question 9

What can be said about the CL on a wing section with strong vortices

The CL will be lower compared to a weaker vortex section

The CL will only change with a change in speed

The CL will be greater compared to a weaker vortex section

The CL will remain unaffected

Answer 9

The CL will be lowest compared to a weaker vortex section

Question 10

Consider a rectangular wing with a span of 13m and a chord of 80cm, what is the Aspect Ratio, to 2 decimal places

Answer 10

16.25

Question 11

Which of the following equations with regards to Bernoulli’s Theorem is correct?

Dynamic pressure = Static pressure - Total pressure

Total pressure = Dynamic pressure - Static pressure

Static pressure = Total pressure + Dynamic pressure

Static pressure = Total pressure - Dynamic pressure

Answer 11

Static pressure = Total pressure - Dynamic pressure

Question 12

Which of the following aircraft designs would be most suited to short field take-offs and landings

high wing, straight wing and plain flaps

high wing, straight wing and slotted flaps

high wing, swept wing and slotted flaps

low wing, straight wing and plain flaps

Answer 12

high wing, straight wing and slotted flaps

Question 13

As alpha decreases, the transition point and stagnation point respectively move;

aft and upwards

forward and upwards

aft and downwards

forward and downwards

Answer 13

aft and upwards

Question 14

Considering an aircraft wing with a large taper and the angle of incidence is constant span wise, where will the wing stall first

At the wingtip

At the mid-point

Along the whole wing at once

At the root

Answer 14

At the wingtip

Question 15

If an aircraft is flying at a constant mach number and enters a warmer air mass, the TAS will (i) and the CAS will (ii)

(i) increase (ii) increase

(i) increase (ii) decrease

(i) increase (ii) remains constant

(i) decrease (ii) increase

Answer 15

(i) increase (ii) remains constant

Question 16

Behind a normal shockwave…

The static pressure will be lower, the mach number will be higher, the density will be higher and the temperature will be lower

The mach number will be lower, the static pressure will be greater, the total pressure energy will be lower and the temperature will be higher

The temperature will be higher, the density will be lower, the total pressure energy will be higher and the LSS will be higher

The dynamic pressure will be higher, the LSS will be lower, the static pressure will be higher and the mach number will be lower

Answer 16

The mach number will be lower, the static pressure will be greater, the total pressure energy will be lower and the temperature will be higher

Question 17

Local Mach numbers are both higher and lower than mach 1.0

At MCRIT

In supersonic flight

At MFS1

At MDRAG DIVERGENCE

In subsonic flight

Answer 17

At MDRAG DIVERGENCE

At MFS1

Question 18

A swept wing aircraft
1. Increases MCRIT
2. Increases VS
3. Produces more lift for a given AoA than a straight wing aircraft
Which of the previous statements are correct or incorrect?

1. incorrect 2. correct 3. incorrect
2. correct 2. correct 3. incorrect
3. correct 2. incorrect 3. incorrect
4. incorrect 2. correct 3. correct

Answer 18

1. correct 2. correct 3. incorrect

Question 19

The buffet free range increases when altitude ……….., when load factor ………. and when CG moves further ……….

Answer 19

decreases

decreases

aft

Question 20

The primary reason for an exceedance of Alpha Crit is too low speed

True

False

Answer 20

True

Question 21

In straight and Level flight the stall speed is 70kts. What is the stall speed at a 30 angle of bank turn

Answer 21

75

Question 22

Stall speed increases with a ……… movement of CG, landing gear ………, ………. thrust, ……….. bank angle

Answer 22

forward

extended

low

increasing

Question 23

Tuck under is caused by

1. which movement of the centre of pressure of the wing and
2. which change of the downwash angle at the location of the stabilizer

(i) aft (ii) increasing

(i) forward (ii) decreasing

(i) aft (ii) decreasing

(i) forward (ii) increasing

Answer 23

(i) aft (ii) decreasing

Question 24

A DA42 has a MTOM of 1999kg. When an instructor and student are in the aircraft it has a TOM of 1340kg. After 1 hour of flight, the aircraft weighs 1260kg and has a stalling speed of 72kts. If they had decided before the flight to take 2 more students with them weighing 145lbs and 180lbs respectively.
What would the new stalling speed by after 1 hour flight time?

81kts

76kts

90kts

68kts

Answer 24

76kts

Question 25

At higher altitudes, the stall speed (IAS) increases decreases until the tropopause decreases remains the same

Answer 25

increases

Question 26

What happens to the aircraft's speed during a developed spin decreases remains relatively stable increases increases and decreases depending on the pitch at a moment in time

Answer 26

remains relatively stable

Question 27

Which of the following statements about stall speed is correct? Decreasing the angle of sweep of the wing will decrease the stall speed Increasing the angle of sweep of the wing will decrease the stall speed Increasing the anhedral of the wing will decrease the stall speed Use of a T-tail will decrease the stall speed

Answer 27

Decreasing the angle of sweep of the wing will decrease the stall speed

Question 28

An object has negatively dynamic stability, the static stability must be negative or positive negative, neutral or positive positive negative

Answer 28

negative or positive

Question 29

The distance between the Aft CG Limit and the Neutral Point is known as the CG range Speed stable range Neutral range Static margin

Answer 29

Static Margin

Question 30

An aircraft is flying with a -B, if the aircraft has directional stability the aircraft will have a tendency to yaw to the left roll to the left yaw to the right roll to the right

Answer 30

yaw to the left

Question 31

Static directional stability increases with Ventral Fin Sweepback Strakes Dorsal Fin High Wing Dihedral

Answer 31

Dorsal Fin Sweepback Ventral Fin Strakes

Question 32

Adverse yaw during a turn entry is caused by increased parasite drag on the raised wing and decreased parasite drag on the lowered wing Increased induced drag on the lowered wing and decreased induced drag on the raised wing decreased induced drag on the lowered wing and increased induced drag on the raised wing decreased induced drag on the raised wing and decreased induced drag on the lowered wing

Answer 32

decreased induced drag on the lowered wing and increased induced drag on the raised wing

Question 33

Comparing the differences between a horizontal trimmable stabiliser and an elevator trim tab, which of these statements are correct or incorrect 1. More drag is produced by a horizontal trimmable stabiliser 2. The effective range of the elevator is less on an THS 1) is incorrect 2) is correct 1) is incorrect 2) is incorrect 1) is correct 2) is correct 1) is correct 2) is incorrect

Answer 33

1) is incorrect 2) is incorrect

Question 34

In an aircraft fitted with spoilers for roll control, and not deployed as speed brakes, a roll to the left is initiated by both spoilers extended right spoiler extended, left spoiler retracted left spoiler extended, but right spoiler extended more left spoiler extended, right spoiler retracted

Answer 34

left spoiler extended, right spoiler retracted

Question 35

The negative Limit Load Factor of a Utility Category aircraft (CS-23) is -4.4 -1.76 -3.0 -1.57

Answer 35

-1.76

Question 36

Which of these statements about the gust load factor on an aeroplane are correct or incorrect? 1. When the wing area decreases, the gust load factor decreases 2. When the EAS decreases, the gust load factor increases 1) is correct 2) is correct 1) is correct 2) is incorrect 1) is incorrect 2) is correct 1) is incorrect 2) is correct

Answer 36

1) is correct 2) is incorrect

Question 37

VRA is the Rough Air Penetration speed. It is the optimum recommended speed for turbulence penetration. Which of the following statements is correct for VRA? VRA must be at least 20% lower than VD VRA must be at least 32% above VA VRA must be less than 0.9VMO VRA must be less than VMO by at least 35kts

Answer 37

VRA must be less than VMO by at least 35kts

Question 38

Which of the following statements is/are correct? On a constant speed propeller, the blade angle of attack is preserved at its optimum (across a wide range of TAS) by altering the blade twist A fixed pitch propeller preserves propeller efficiency over a wide range of airspeeds The adjustable pitch propeller allows the blade pitch angle to be manually adjusted by the pilot using a pitch control lever On a fixed pitch propeller, there is only one TAS and RPM setting at which the angle of attack is optimum

Answer 38

The adjustable pitch propeller allows the blade pitch angle to be manually adjusted by the pilot using a pitch control lever On a fixed pitch propeller, there is only one TAS and RPM setting at which the angle of attack is optimum

Question 39

Which of the following statements is incorrect? If the total reaction is inclined forwards, then the proportion of thrust will increase Blade icing reduced efficiency and may also cause early boundary layer separation A variable pitch propeller operates at high levels of efficiency at only one combination of propeller RPM and TAS Excessively fine pitch results in low torque drag which increases the risk of over-speeding the engine

Answer 39

A variable pitch propeller operates at high levels of efficiency at only one combination of propeller RPM and TAS

Question 40

The phenomenon where the aircraft tries to rotate in the opposite direction from the propeller is called ............... This can produce a ........... when on the ground during the take-off run. On light twin aircraft this effect can be reduced by using ................ propellers

Answer 40

torque effect yaw counter-rotating

Question 41

An Airbus A320 takes off with a mass of 69,500kg. The thrust per engine in the climb is 109kN. The total drag produced in the climb is 77.5kN. Assuming that the total drag is not affected, what would be the reduction in the climb gradient if one engine fails? Assume 1g = 10m/s 157% 4.5% 15.7% 20.2%

Answer 41

15.7%

Question 42

Considering an aircraft flying at VMC, which of the following is not a risk or hazard to the aircraft? Large fin loads Increasing sideslip Excessive Beta Angle at the fin low angle of attack

Answer 42

low angle of attack

Question 43

By what percentage does the lift increase in a level turn at 65 angle of bank, compared to straight and level flight 58% 36% 42% 136%

Answer 43

136%

Question 44

An aircraft is in an uncoordinated turn to the right and is skidding Which of the below statements is correct? The aircraft has too little bank Right rudder needs to be applied Speed needs to be increased The aircraft has too much bank

Answer 44

The aircraft has too little bank

Question 45

An aircraft in a wings level climb at constant IAS and mass, what happens to the angle of climb The angle of climb will only change with a change in IAS It reduces It increases It remains constant

Answer 45

It reduces