Module 8 Set 7 AST

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1
The angle of attack of an aircrafts tailplane will influence its
  • Directional stability
  • Lateral stability
  • Longitudinal stability
2
When an aircraft is disturbed in pitch and its dynamic response is to continually move away from datum it has
  • Negative dynamic longitudinal stability
  • Neutral dynamic lateral stability
  • Positive dynamic stability
3
To balance out variations in pitching moment due to movement of the center of pressure a
  • Rudder is fitted
  • Fin is fitted
  • Tailplane is fitted
4
Longitudinal stability is about the
  • Longitudinal axis and is achieve using the horizontal stabilizer
  • Lateral axis and is achieved using the tailplane
  • Normal axis and is achieved using the vertical stabilizer
5
Stability in pitch
  • Longitudinal stability about the lateral axis
  • Lateral stability about the lateral axis
  • Lateral stability about the longitudinal axis
6
The horizontal stabilizer will help with
  • Stability about the longitudinal axis
  • Stability about the lateral axis
  • Drag limitation in the main aircraft structure
7
If an aircraft is displaced nose-up and the wing downwash angle is increased, the
  • Tailplane angle of attack is increased, increasing total tail lift
  • Tailplane angle of attack is increased but the restoring moment is reduced
  • Effective tailplane angle of attack and restoring moment is reduced
8
Directional stability is achieved by controlling
  • Yawing motion about the vertical axis only
  • Rolling motion about the longitudinal axis only
  • Yawing motion about the longitudinal axis only
9
The function of the vertical stabilizer is to promote directional stability about the
  • Longitudinal axis
  • Lateral axis
  • Normal axis
10
The function of the vertical stabilizer is to promote
  • Longitudinal stability about the lateral axis
  • Lateral stability about the longitudinal axis
  • Directional stability about the normal axis
11
Directional stability of an aircraft is determined by
  • Fin area and moment arm
  • Wing area divided by fin area
  • Ratio of tailplane volume to the fin volume
12
The fin provides an aircraft with
  • Lateral stability
  • Longitudinal stability
  • Directional stability
13
The vertical stabilizer is considered a
  • Secondary control surface and will be used for static longitudinal stability
  • Primary control surface and will be used for static directional stability
  • Primary control surface and will be used for dynamic lateral stability
14
An aircrafts keel surface aft of its C of G assists in providing
  • Directional stability about the normal axis
  • Longitudinal stability about the normal axis
  • Lateral stability about the vertical axis
15
Lateral stability may be provided by the
  • Wing dihedral
  • Horizontal stabiliser
  • Ailerons
16
Several factors affect the static lateral stability of an aircraft such as wing/fuselage interference. Others in the correct combination are
  • Tail area, tail volume and sweepback
  • Dihedral, sweepback and fuselage/vertical stabiliser contribution
  • Weathercock stability, wing downwash and planform
17
An aircraft constructed with dihedral will provide
  • Lateral stability about the longitudinal axis
  • Longitudinal stability about the lateral axis
  • Lateral stability about the normal axis
18
A dihedral angle wing
  • Gives a greater lift force to the down-going wing in a roll
  • Gives a greater lift force to the up-going wing in a roll
  • Does not affect the lift force of a wing until the spoilers are activated
19
On an aircraft with a dihedral wing, sideslip will produce a stable
  • Pitching moment
  • Rolling moment
  • Yawing moment
20
If an aircraft has to much dihedral effect, it will tend to
  • Roll
  • Be easy to maneuver
  • Dutch roll instability
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