FAA Airman Knowledge Test Bank a well
detailed practice exam 2025/2026 graded
A+ well written !!! Advanced
Comprehensive Examination 150 Multiple-
Choice Questions with Answers and
Rationales
SECTION 1: AERODYNAMICS (Questions 1–20)
1. Within what Mach range does transonic flight regimes usually occur?
A) 1.20 to 2.50 Mach
B) 0.50 to 0.75 Mach
C) 0.75 to 1.20 Mach
Correct Answer: C
Rationale: Transonic flight occurs in the Mach range where airflow over the aircraft surface
transitions between subsonic and supersonic, typically from approximately Mach 0.75 to Mach
1.20. In this regime, mixed subsonic and supersonic flow exists over the airframe, leading to
compressibility effects such as shock wave formation and drag divergence.
2. How does VNE speed vary with altitude?
,A) Remains the same at all altitudes
B) Varies directly with altitude
C) Varies inversely with altitude
Correct Answer: A
Rationale: VNE (Never Exceed Speed) remains constant regardless of altitude. While true
airspeed increases with altitude for a given indicated airspeed, the structural limitation VNE is
defined in terms of indicated airspeed and does not change with density altitude.
3. Which is a purpose of wing-mounted vortex generators?
A) Delays the onset of drag divergence at high speeds and aids in maintaining aileron
effectiveness at high speeds
B) Breaks the airflow over the wing so the stall will progress from the root out to the tip of the
wing
C) Increase the onset of drag divergence and aid in aileron effectiveness at low speed
Correct Answer: A
Rationale: Vortex generators energize the boundary layer by creating small vortices, which
delays flow separation and drag divergence at high speeds while maintaining aileron
effectiveness. This improves control authority and high-speed handling characteristics.
4. What is the effect on total drag of an aircraft if the airspeed decreases in level flight below
that speed for maximum L/D?
A) Drag increases because of increased parasite drag
B) Drag decreases because of lower induced drag
C) Drag increases because of increased induced drag
Correct Answer: C
Rationale: Below the speed for maximum L/D, induced drag increases exponentially as angle of
attack must increase to maintain lift. This occurs because the wing must generate the same
amount of lift at a higher coefficient of lift, which increases induced drag.
5. What is the condition that may occur when gusts cause a swept wing type airplane to roll in
one direction while yawing in the other?
,A) Wingover
B) Mach buffet
C) Dutch roll
Correct Answer: C
Rationale: Dutch roll is a coupled lateral-directional oscillation where the aircraft rolls in one
direction while yawing in the other. Swept-wing aircraft are particularly susceptible to this
condition due to the inherent yaw-roll coupling characteristics of swept wings.
6. What is the relationship of the rate of turn with the radius of turn with a constant angle of
bank but increasing airspeed?
A) Rate will decrease and radius will increase
B) Rate and radius will increase
C) Rate will increase and radius will decrease
Correct Answer: A
Rationale: With constant bank angle and increasing airspeed, the rate of turn decreases while
the radius of turn increases. This is because turn rate is inversely proportional to speed, while
radius is directly proportional to speed squared for a given bank angle.
7. By changing the angle of attack of a wing, the pilot can control the airplane's:
A) Lift, gross weight, and drag
B) Lift and airspeed, but not drag
C) Lift, airspeed, and drag
Correct Answer: C
Rationale: Angle of attack directly influences lift coefficient, which affects both lift and induced
drag. Changing angle of attack also alters airspeed as the aircraft seeks equilibrium, making all
three parameters (lift, airspeed, and drag) controllable through AOA manipulation.
8. What is the result of a shock-induced separation of airflow occurring symmetrically near
the wing root of a sweptwing aircraft?
, A) A high-speed stall and sudden pitchup
B) Severe porpoising
C) A severe moment or 'Mach tuck'
Correct Answer: A
Rationale: Symmetric shock-induced separation near the wing root causes the center of
pressure to move aft, resulting in a sudden pitchup and high-speed stall. This is a dangerous
condition that can occur during high-speed, high-altitude flight.
9. What is a characteristic of longitudinal instability?
A) Bank oscillations becoming progressively greater
B) Aircraft constantly tries to pitch down
C) Pitch oscillations becoming progressively greater
Correct Answer: C
Rationale: Longitudinal instability is characterized by pitch oscillations that become
progressively greater in amplitude. This is a dynamic stability issue where the aircraft's natural
tendency to return to equilibrium is insufficient, leading to diverging pitch oscillations.
10. Identify the type of stability if the aircraft attitude tends to move farther from its original
position after a disturbance:
A) Positive stability
B) Neutral stability
C) Negative stability
Correct Answer: C
Rationale: Negative stability (instability) occurs when the aircraft continues to move away from
its original attitude after a disturbance. This is the opposite of positive stability, where the
aircraft returns to its original state.
11. What is the primary aerodynamic effect of flaps during approach and landing?
A) Increase stall speed and decrease drag
B) Decrease stall speed and increase lift and drag
C) Increase both lift and stall speed
detailed practice exam 2025/2026 graded
A+ well written !!! Advanced
Comprehensive Examination 150 Multiple-
Choice Questions with Answers and
Rationales
SECTION 1: AERODYNAMICS (Questions 1–20)
1. Within what Mach range does transonic flight regimes usually occur?
A) 1.20 to 2.50 Mach
B) 0.50 to 0.75 Mach
C) 0.75 to 1.20 Mach
Correct Answer: C
Rationale: Transonic flight occurs in the Mach range where airflow over the aircraft surface
transitions between subsonic and supersonic, typically from approximately Mach 0.75 to Mach
1.20. In this regime, mixed subsonic and supersonic flow exists over the airframe, leading to
compressibility effects such as shock wave formation and drag divergence.
2. How does VNE speed vary with altitude?
,A) Remains the same at all altitudes
B) Varies directly with altitude
C) Varies inversely with altitude
Correct Answer: A
Rationale: VNE (Never Exceed Speed) remains constant regardless of altitude. While true
airspeed increases with altitude for a given indicated airspeed, the structural limitation VNE is
defined in terms of indicated airspeed and does not change with density altitude.
3. Which is a purpose of wing-mounted vortex generators?
A) Delays the onset of drag divergence at high speeds and aids in maintaining aileron
effectiveness at high speeds
B) Breaks the airflow over the wing so the stall will progress from the root out to the tip of the
wing
C) Increase the onset of drag divergence and aid in aileron effectiveness at low speed
Correct Answer: A
Rationale: Vortex generators energize the boundary layer by creating small vortices, which
delays flow separation and drag divergence at high speeds while maintaining aileron
effectiveness. This improves control authority and high-speed handling characteristics.
4. What is the effect on total drag of an aircraft if the airspeed decreases in level flight below
that speed for maximum L/D?
A) Drag increases because of increased parasite drag
B) Drag decreases because of lower induced drag
C) Drag increases because of increased induced drag
Correct Answer: C
Rationale: Below the speed for maximum L/D, induced drag increases exponentially as angle of
attack must increase to maintain lift. This occurs because the wing must generate the same
amount of lift at a higher coefficient of lift, which increases induced drag.
5. What is the condition that may occur when gusts cause a swept wing type airplane to roll in
one direction while yawing in the other?
,A) Wingover
B) Mach buffet
C) Dutch roll
Correct Answer: C
Rationale: Dutch roll is a coupled lateral-directional oscillation where the aircraft rolls in one
direction while yawing in the other. Swept-wing aircraft are particularly susceptible to this
condition due to the inherent yaw-roll coupling characteristics of swept wings.
6. What is the relationship of the rate of turn with the radius of turn with a constant angle of
bank but increasing airspeed?
A) Rate will decrease and radius will increase
B) Rate and radius will increase
C) Rate will increase and radius will decrease
Correct Answer: A
Rationale: With constant bank angle and increasing airspeed, the rate of turn decreases while
the radius of turn increases. This is because turn rate is inversely proportional to speed, while
radius is directly proportional to speed squared for a given bank angle.
7. By changing the angle of attack of a wing, the pilot can control the airplane's:
A) Lift, gross weight, and drag
B) Lift and airspeed, but not drag
C) Lift, airspeed, and drag
Correct Answer: C
Rationale: Angle of attack directly influences lift coefficient, which affects both lift and induced
drag. Changing angle of attack also alters airspeed as the aircraft seeks equilibrium, making all
three parameters (lift, airspeed, and drag) controllable through AOA manipulation.
8. What is the result of a shock-induced separation of airflow occurring symmetrically near
the wing root of a sweptwing aircraft?
, A) A high-speed stall and sudden pitchup
B) Severe porpoising
C) A severe moment or 'Mach tuck'
Correct Answer: A
Rationale: Symmetric shock-induced separation near the wing root causes the center of
pressure to move aft, resulting in a sudden pitchup and high-speed stall. This is a dangerous
condition that can occur during high-speed, high-altitude flight.
9. What is a characteristic of longitudinal instability?
A) Bank oscillations becoming progressively greater
B) Aircraft constantly tries to pitch down
C) Pitch oscillations becoming progressively greater
Correct Answer: C
Rationale: Longitudinal instability is characterized by pitch oscillations that become
progressively greater in amplitude. This is a dynamic stability issue where the aircraft's natural
tendency to return to equilibrium is insufficient, leading to diverging pitch oscillations.
10. Identify the type of stability if the aircraft attitude tends to move farther from its original
position after a disturbance:
A) Positive stability
B) Neutral stability
C) Negative stability
Correct Answer: C
Rationale: Negative stability (instability) occurs when the aircraft continues to move away from
its original attitude after a disturbance. This is the opposite of positive stability, where the
aircraft returns to its original state.
11. What is the primary aerodynamic effect of flaps during approach and landing?
A) Increase stall speed and decrease drag
B) Decrease stall speed and increase lift and drag
C) Increase both lift and stall speed
