AT 116 Exam 2 Review | Principles of
Athletic Training and Injury Management
Questions and Answers Latest
T/F Wing dihedral is one of the ways that we achieve stability around the longitudinal axis -
** True
E: Roll stability on a low wing aircraft is corrected using a dihedral wing angle. In normal flight the
Bernoulli effect (lift) does not pull straight up, it pulls up and in-board.
If the aircraft rolls, one wing is directly opposing weight, while the other is slanted. This allows the
wing to roll back into level flight.
T/F Wing dihedral must be greater on an aircraft that has the wings mounter higher. -
** True
E: Ask
How does dihedral make an airplane stable? -
** The wing that falls, results in a Bernoulli force that directly opposes gravity, and lifts the wing
back up.
Why would we want anhedral on a wing? -
** The aircraft has a very heavy and low center of gravity
E: When the aircraft becomes too stable, anhedral is used to destabilize the aircraft and adds
maneuverability.
With negative dihedral in flight (LEVEL), the Bernoulli effect pulls up and outboard.
Which of the following is NOT one of the ways that an airplane gains stability around the vertical
axis? -
** Move the center of gravity behind the center of lift.
,E: We get stability around the vertical axis in TWO ways:
1) Use the vertical stabilizer (If the aircraft yaws one way... Camber airflow on one side increases...
Bernoulli one side 1 increases... Bernoulli on side 2 decreases... this creates sideways lift... which
pulls the aircraft back straight)
2) Swept back wings (Changes the induced drag and parasite drag on each side).
If an aircraft has positive dynamic stability, which is true of the aircraft? -
** The aircraft returns to straight and level through a series of constantly reducing oscillations
E: Static Stability (Does the object attempt to return to its NULL or HOME if displaced), Dynamic
Stability (Describe how it returns home, through positive static stability)
If an aircraft has neutral static stability, which is true of the aircraft? -
** The aircraft does not display any tendency to return to straight and level but stays at whatever
altitude it is placed.
E: Positive static (If displaced it will try to return home)
Neutral static (If displaced it will stay at the displaced position) Negative Static (Will not try to stay at
null even if displaced).
.T/F Under a positive G load maneuver, the pilot feels lighter in the seat? -
** False
E: the pilot should feel heavier. You should feel a downward force on the aircraft. The pilot is
typically pitching up.
T/F The smaller the radius of a turn, the greater the G forces? -
** True
E: The tighter the radius the bigger the G. The bigger the radius the smaller the G. G- load is a
function of the speed of the aircraft and radius of the circle of the turn.
, T/F Static stability describes how an object returns to its home state or "null" -
** False
E: Static is "Does the object attempt to return to null. Dynamic describes how it returns to null.
How do we create yaw stability on an aircraft -
** Only a and b are correct (put a vertical stabilizer on the tail of the aircraft and sweep the wings
backward)
E:1) Use the vertical stabilizer (If the aircraft yaws one way... Camber airflow on one side increases...
Bernoulli one side 1 increases... Bernoulli on side 2 decreases... this creates sideways lift... which
pulls the aircraft back straight)
2) Swept back wings (Changes the induced drag and parasite drag on each side).
What produces pitch stability on a standard aircraft? -
** Both B and C are correct (The horizontal stabilizer pulls down and using a dihedral wing angle)
E: Pitch stability is primarily due to the constant downward pull on the tail, and small automatic
changes on the horizontal tail, preventing the CG from oscillating up and down
T/F Pitch stability is considered to be longitudinal stability? -
** True
E:
Yaw= Stability around the vertical axis (Directional Stability)
Pitch= Stability around the lateral axis (Longitudinal Stability)
Roll= Stability around the Longitudinal axis (Lateral Stability)
Which of the following is not an advantage of a high wing aircraft? -
** Easier to build strong landing gear support
Athletic Training and Injury Management
Questions and Answers Latest
T/F Wing dihedral is one of the ways that we achieve stability around the longitudinal axis -
** True
E: Roll stability on a low wing aircraft is corrected using a dihedral wing angle. In normal flight the
Bernoulli effect (lift) does not pull straight up, it pulls up and in-board.
If the aircraft rolls, one wing is directly opposing weight, while the other is slanted. This allows the
wing to roll back into level flight.
T/F Wing dihedral must be greater on an aircraft that has the wings mounter higher. -
** True
E: Ask
How does dihedral make an airplane stable? -
** The wing that falls, results in a Bernoulli force that directly opposes gravity, and lifts the wing
back up.
Why would we want anhedral on a wing? -
** The aircraft has a very heavy and low center of gravity
E: When the aircraft becomes too stable, anhedral is used to destabilize the aircraft and adds
maneuverability.
With negative dihedral in flight (LEVEL), the Bernoulli effect pulls up and outboard.
Which of the following is NOT one of the ways that an airplane gains stability around the vertical
axis? -
** Move the center of gravity behind the center of lift.
,E: We get stability around the vertical axis in TWO ways:
1) Use the vertical stabilizer (If the aircraft yaws one way... Camber airflow on one side increases...
Bernoulli one side 1 increases... Bernoulli on side 2 decreases... this creates sideways lift... which
pulls the aircraft back straight)
2) Swept back wings (Changes the induced drag and parasite drag on each side).
If an aircraft has positive dynamic stability, which is true of the aircraft? -
** The aircraft returns to straight and level through a series of constantly reducing oscillations
E: Static Stability (Does the object attempt to return to its NULL or HOME if displaced), Dynamic
Stability (Describe how it returns home, through positive static stability)
If an aircraft has neutral static stability, which is true of the aircraft? -
** The aircraft does not display any tendency to return to straight and level but stays at whatever
altitude it is placed.
E: Positive static (If displaced it will try to return home)
Neutral static (If displaced it will stay at the displaced position) Negative Static (Will not try to stay at
null even if displaced).
.T/F Under a positive G load maneuver, the pilot feels lighter in the seat? -
** False
E: the pilot should feel heavier. You should feel a downward force on the aircraft. The pilot is
typically pitching up.
T/F The smaller the radius of a turn, the greater the G forces? -
** True
E: The tighter the radius the bigger the G. The bigger the radius the smaller the G. G- load is a
function of the speed of the aircraft and radius of the circle of the turn.
, T/F Static stability describes how an object returns to its home state or "null" -
** False
E: Static is "Does the object attempt to return to null. Dynamic describes how it returns to null.
How do we create yaw stability on an aircraft -
** Only a and b are correct (put a vertical stabilizer on the tail of the aircraft and sweep the wings
backward)
E:1) Use the vertical stabilizer (If the aircraft yaws one way... Camber airflow on one side increases...
Bernoulli one side 1 increases... Bernoulli on side 2 decreases... this creates sideways lift... which
pulls the aircraft back straight)
2) Swept back wings (Changes the induced drag and parasite drag on each side).
What produces pitch stability on a standard aircraft? -
** Both B and C are correct (The horizontal stabilizer pulls down and using a dihedral wing angle)
E: Pitch stability is primarily due to the constant downward pull on the tail, and small automatic
changes on the horizontal tail, preventing the CG from oscillating up and down
T/F Pitch stability is considered to be longitudinal stability? -
** True
E:
Yaw= Stability around the vertical axis (Directional Stability)
Pitch= Stability around the lateral axis (Longitudinal Stability)
Roll= Stability around the Longitudinal axis (Lateral Stability)
Which of the following is not an advantage of a high wing aircraft? -
** Easier to build strong landing gear support
