# Aerodynamics (part 2) Flashcards

1
Q

What situations may result in load factors reaching the maximum or being exceeded? (FAA-H-8083-25)

A
1. Level turns (load factor in a 60°-bank turn is 2 Gs)
2. Heavy turbulence
3. Speeds above maneuvering speed
2
Q

What effect does an increase in load factor have on stalling speed? (FAA-H-8083-25)

A
1. As load factor increases, stalling speed increases
3
Q

Define the term maneuvering speed. (FAA-H-8083-25, SAIB CE-11-17)

A
1. The maximum speed at which full deflection of the control surfaces can be imposed without causing structural damage
2. Speeds below the maneuvering speed, allow an aircraft to stall prior to structural damage of the aircraft
3. Maneuvering speed increases with an increase in weight
4
Q

Define loss-of-control-inflight (LOC-I). (FAA-H-8083-3)

A
1. LOC-I is defined as a significant deviation of an aircraft from the intended flight path
5
Q

What causes an airplane to stall? (FAA-H-8083-25)

A
1. Exceeding the critical angle of attack
2. This critical angle of attack varies from 16° to 20° depending on the airplane’s design
3. The critical angle of attack where the stall occurs is the same, regardless of airspeed, weight, load factor, or density altitude
6
Q

What is a spin? (AC61-67)

A
1. A spin is a maneuver in which the airplane descends in a helical path while stalled
2. Spins result from aggravated stalls in either a slip or a skid
3. If a stall does not occur, a spin cannot occur
7
Q

When are spins most likely to occur? (AC61-67)

A
1. A stall/spin situation can occur in any phase of flight but is most likely to occur in the following situations:
2. Turn from base to final (slipping or skidding turn)
3. Engine failure on takeoff during climb out (pilot makes an uncoordinated turn back to departure runway)
4. Engine failure on approach to landing (pilot tries to stretch glide to runway by increasing back pressure)
5. Go-around with improper flap retraction
8
Q

What procedure should be used to recover from an inadvertent spin? (AC61-67)

A
1. P A R E
2. Power—reduce to idle
3. Ailerons—position to neutral
4. Rudder—apply full opposite against rotation
5. Elevator—apply positive movement to break stall
6. Once the spin rotation stops, neutralize the rudder, and return to level flight
9
Q

A
1. When turning an airplane to the left, the downward deflected aileron on the right produces more lift and more drag on the right wing
2. This added lift and drag attempts to pull or veer the airplane’s nose in the direction of the raised wing (right)
10
Q

What is ground effect? (FAA-H-8083-3)

A
1. While in ground effect, a change occurs in the airflow pattern around the airplane because it is restricted around the wing by the surface of the ground
2. This reduces the wing’s upwash, downwash, and wingtip vortices, therefore increasing performance/efficiency
11
Q

What major problems can be caused by ground effect? (FAA-H-8083-3)

A
1. Any excess speed landing may result in a significant float distance
2. Due to reduced drag in ground effect, the aircraft may seem capable of takeoff well below recommended speed