Mnemonics and Main Memory Items | Performance

Question 1

The effect of landing gear on total drag and Vmd -

Answer 1

total drag increase and Vmd decreases

Question 2

The coefficient of lift (CL) is the ratio between -

Answer 2

lift per unit wing area and dynamic pressure

Question 3

As the angle of attack increases from -4°, the leading edge stagnation point moves from the
_____ surface around the leading edge to the _____ surface.

Answer 3

As the angle of attack increases from -4°, the leading edge stagnation point moves from the
upper surface around the leading edge to the lower surface.`

Question 4

Main effect when in ground effect:

Answer 4

1. Reduced induced drag
2. Increase in effective angle of attack
3. Stalling angle decreases
4. Decreased effective angle of attack of the tail-plane, resulting in pitch up moment
5. ASI and altimeter under-read

Question 5

Camber line and chord line:

Answer 5

A line connecting the leading and trailing edge midway between the upper and lower surface of an aerofoil is the camber line.

Chord line is the same but straight

Question 6

The best ROC speed with altitude will -

Answer 6

increase

Question 7

In a glide, added weight will reduce?

Answer 7

The glide endurance

Question 8

A heavier aircraft will have a _____(vmd speed)?

Answer 8

maximum lift/drag ratio airspeed

Question 9

during a glide, the distance flown compared to increased weight?

Answer 9

Unchanged

Question 10

How to calculate the stalling speed in a turn?

Answer 10

New stalling speed = Old stalling speed x square root of load factor

Question 11

Does an increase in weight affect the gliding angle

Answer 11

No, since it depends on the lift/drag ratio.

Note: The lift/drag ratio is independent of weight. An increase in weight needs a corresponding increase in total lift and, consequently, a greater lift and drag will result. The proportions remain exactly the same and the L/D ratio and glide angle thus remain unaltered.

Question 12

Vref is?

Answer 12

1.3 Vso

Question 13

V2min definition -

V2MIN may not be less than:

• ___VSR for 2 and 3 engine turboprops and all turbojets without provision for obtaining
a significant reduction in the one engine inoperative power-on stalling speed OR ___VSR
for turboprops with more than 3 engines and turbojets with provision for obtaining a
significant reduction in the one engine inoperative power-on stalling speed.
• ___VMC
3. ___ VS
4. ___VS for turbo-prop more than 3 engines

Answer 13

The minimum take-off safety speed, with the critical engine inoperative.

V2MIN may not be less than:

1. 1.13VSR for 2 and 3 engine turboprops and all turbojets without provision for obtaining
   a significant reduction in the one engine inoperative power-on stalling speed OR 1.08VSR
   for turboprops with more than 3 engines and turbojets with provision for obtaining a
   significant reduction in the one engine inoperative power-on stalling speed.
2. 1.1VMCA
3. 1.2 VS
4. 1.15VS for turbo-prop more than 3 engines

Question 14

V2 should not be less than?

Answer 14

V2min

Question 15

V2 must be __ faster than the Vso

Answer 15

V2 must be 20% faster than the stall speed

Question 16

V2 must be __ higher than Vmca

Answer 16

V2 must be 10% higher than Vmca

Question 17

Vr may not be less than ____ Vmcg

Answer 17

105% Vmcg

Question 18

How is VMCA influenced by increasing pressure altitude?

Answer 18

A
VMCA decreases with increasing pressure altitude

Any engine failure on a multi-engine aircraft will result in a yaw toward the inoperative engine.

As Pressure Altitude increases, asymmetric thrust decreases. As thrust decreases, the operative engine requires less rudder authority to

maintain directional stability thus allowing the aircraft to maintain directional authority at lower indicated airspeeds.

Therefore, VMCA will decrease with an increase in Pressure Altitude.

Question 19

VR may not be less than:

• __
• ___ VMC
• a speed such that __ may be attained before __ ft.
• a speed such that if the aeroplane is rotated at its maximum practicable rate the result will
be a VLOF of not less than 1.1VMU (all engines operating) or 1.05VMU (engine inoperative) [ if
the aeroplane is geometry limited or elevator power limited these margins are 1.08VMU (all
engines) and 1.04VMU (engine inoperative)]

Answer 19

VR may not be less than:
• V1
• 1.05VMCA
• a speed such that V2may be attained before 35 ft.
• a speed such that if the aeroplane is rotated at its maximum practicable rate the result will be a VLOF of not less than 1.1VMU (all engines operating) or 1.05VMU (engine inoperative) [ if the aeroplane is geometry limited or elevator power limited these margins are 1.08VMU (all engines) and 1.04VMU (engine inoperative)]

Question 20

The aerodynamic ceiling is -

Answer 20

is the altitude at which the speeds for low speed buffet and for high speed buffet are the same

Question 21

Handy rule of thumb for ROD:

Answer 21

Multiply your Groundspeed by 5 to get the approximate Rate of Descent

90 x 5 = 450fpm

Question 22

LDR is the horizontal distance required to land and stop completely from a point -

Answer 22

50 ft above the landing surface