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AT 116 EXAM 2 QUESTIONS WITH 100% VERIFIED ANSWERS
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AT 116 EXAM 2 QUESTIONS WITH 100%VERIFIED ANSWERS
T/F Wing dihedral is one of the ways that we achieve stability around the
longitudinal axis - ANSWER 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. - ANSWER True
E: Ask
How does dihedral make an airplane stable? - ANSWER 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? - ANSWER 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? - ANSWER 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? -
ANSWER 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? -
ANSWER 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? -
ANSWER 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? - ANSWER 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" -
ANSWER 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 - ANSWER 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? - ANSWER 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? - ANSWER 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? - ANSWER
Easier to build strong landing gear support
E: Advantages of a high wing aircraft
1) Better lift/drag ratio
2) Better lateral (roll) stability
3) Shorter landing distance
Which of the following is not an advantage of a low wing aircraft? - ANSWER
Better lift/drag ratio
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