Stability Flashcards

1
Q

The distance between the CG and neutral point is called the ___ __ and is expressed as a percentage MAC

A

static margin

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2
Q

The forward limit of the static margin is usually determined by ___

A
  • A fast enough pitching rate

- A control force that is not too high

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3
Q

The aft limit of the static margin is usually determined by ___

A
  • Not exceeding a certain pitching rate

- A control force that is not too low

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4
Q

Lowering flaps will move the CP ___wards

A

rearwards

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5
Q

Extension of the landing gear will cause a nose ___ pitching moment, __creasing the tail down force

A

down, increasing

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6
Q

Damping __creases with altitude

A

decreases

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7
Q

Swept finds stall at a ___ angle of attack

A

higher

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8
Q

Explain the purpose of dorsal and ventral fins

A

They increase the direction stability during extreme sideslip conditions

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9
Q

The ventral fin has its greatest effect when flying at ___ pitch angles

A

high

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10
Q

The purpose of vortex strakes is to ___

A

Reduce yawing disturbance caused by the crossflow generated by aircraft with long noses at high AoA

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11
Q

The dihedral is the angle between ___

A

the 0.25 chord line of the wing and lateral axis

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12
Q

A ___ wingspan has a greater lateral stability

A

larger

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13
Q

Spiral instability occurs when __ stability is too great compared to ___ stability

A

directional, lateral

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14
Q

Dutch roll occurs when ___ stability is too great

A

lateral

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15
Q

Sweepback and dihedral increase the ___ stability only

A

lateral

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16
Q

With increasing altitude at constant IAS, the static lateral stability will ___ and the dynamic directional stability will ___

A

increase, decrease

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17
Q

With increasing altitude at constant Mach number, the static lateral stability will ___ and the aerodynamic damping is ___ meaning the dynamic directional-lateral stability will ___

A

not change, reduced, reduce

18
Q

Static stick force stability can be recognised by having to ___ the control column to maintain a speed above the trim

19
Q

The effect of wing downwash on static longitudinal sability is ___

20
Q

A swept/straight wing and a high/low aspect ratio are the least affected by turbulence

A

swept, low

21
Q

Stick force stability means ___

A

with higher airspeed, you’re required to push further forward on the control column to keep the aircraft in straight and level flight.

22
Q

Negative stick force stability can be found during ___ flight as more ___ is required to keep the nose from dropping at high speeds

A

transonic, stick pulling, rather than pushing

23
Q

An inset hinge provides ___

A

aerodynamic balance

24
Q

A positive camber has ___ effect on longitudinal stability

25
The pitching moment about the aerodynamic centre is always ___, regardless of angle of attack.
negative
26
Phugoid damping is normally ___
weak
27
Short period damping is normally ___
significant
28
Speed and altitude vary ___ during the short period oscillation
slightly
29
Speed and altitude vary ___ during the phugoid
significant
30
Dorsal and ventral fins have a ___ effect on longitudinal stability, a ___ effect on lateral stability, and a ___ effect on directional stability
neutral, negative, positive
31
The wing sweep angle is the angle between the ___ and the ___
quarter chord and the wing lateral axis
32
Stick force stability depends on ___ stability
longitudinal
33
Stick force stability is determined by the distance from ___ to the ___
neutral point CG
34
A CG which is further forward means a ___ stick force stability
higher
35
Manoeuvre stability will ___ with the static margin
increase
36
The static margin is the distance from the ___ to the ___
manoeuvre point, CG
37
Positive stick position stability means ___
that you pull back on the stick if the speed decreases, and push forward if it increases
38
Fully hydraulic flight controls (don't) require mass balancing
they do
39
With increasing altitude and constant IAS, an aircraft with swept back wings will see ___ static lateral stability and ___ dynamic lateral-directional stability
increasing, decreasing
40
With increasing altitude and constant Mach number, an aircraft with swept back wings will see ___ static lateral stability and ___ dynamic lateral-directional stability
no change in, decreasing