1The angle of attack of an aircrafts tailplane will influence its
- Directional stability
- Lateral stability
- Longitudinal stability
2When 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
3To balance out variations in pitching moment due to movement of the center of pressure a
- Rudder is fitted
- Fin is fitted
- Tailplane is fitted
4Longitudinal 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
5Stability in pitch
- Longitudinal stability about the lateral axis
- Lateral stability about the lateral axis
- Lateral stability about the longitudinal axis
6The horizontal stabilizer will help with
- Stability about the longitudinal axis
- Stability about the lateral axis
- Drag limitation in the main aircraft structure
7If 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
8Directional 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
9The function of the vertical stabilizer is to promote directional stability about the
- Longitudinal axis
- Lateral axis
- Normal axis
10The 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
11Directional 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
12The fin provides an aircraft with
- Lateral stability
- Longitudinal stability
- Directional stability
13The 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
14An 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
15Lateral stability may be provided by the
- Wing dihedral
- Horizontal stabiliser
- Ailerons
16Several 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
17An aircraft constructed with dihedral will provide
- Lateral stability about the longitudinal axis
- Longitudinal stability about the lateral axis
- Lateral stability about the normal axis
18A 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
19On an aircraft with a dihedral wing, sideslip will produce a stable
- Pitching moment
- Rolling moment
- Yawing moment
20If an aircraft has to much dihedral effect, it will tend to
- Roll
- Be easy to maneuver
- Dutch roll instability