FAA Airman Knowledge Test Bank V3.1 a
well detailed exam 2025/2026 graded A+
upgraded !!! Advanced Comprehensive
Examination — 150 Questions with
Detailed Answers and Rationales
SECTION 1: AERODYNAMICS AND PRINCIPLES OF FLIGHT (Questions 1–20)
1. When an aircraft is in steady, unaccelerated flight, the relationship between the four forces
is:
A) Lift equals weight; thrust equals drag
B) Lift is greater than weight; thrust is greater than drag
C) Lift is less than weight; thrust is less than drag
D) Lift equals thrust; weight equals drag
Correct Answer: A
Rationale: In steady, unaccelerated flight, all forces are in equilibrium: lift exactly balances
weight, and thrust exactly balances drag. This fundamental relationship is essential for
understanding performance, stability, and control. Any imbalance results in acceleration or
deceleration.
2. What is the effect on total drag of an aircraft if the airspeed decreases in level flight below
the 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
D) Drag remains constant because total drag is minimized
Correct Answer: C
Rationale: Below the speed for maximum L/D, induced drag increases exponentially as angle of
attack must increase to maintain lift. The wing must generate the same lift at a higher
coefficient of lift, which dramatically increases induced drag. Parasite drag decreases with lower
speed, but the induced drag increase is more significant.
3. What is the condition that may occur when gusts cause a swept-wing airplane to roll in one
direction while yawing in the other?
A) Wingover
B) Mach buffet
C) Dutch roll
D) Spiral instability
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 due to the
inherent yaw-roll coupling characteristics. The oscillation can be uncomfortable and, if severe,
may lead to loss of control.
4. 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
D) Rate will remain constant while radius increases
Correct Answer: A
Rationale: With constant bank angle and increasing airspeed, the rate of turn decreases while
the radius of turn increases. Turn rate is inversely proportional to speed (Rate = g × tan(φ) / V),
,while radius is directly proportional to speed squared (R = V² / (g × tan(φ))) for a given bank
angle.
5. 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
D) Only lift, as airspeed and drag are fixed
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 in the lift
equation L = CL × ½ρV² × S. All three parameters (lift, airspeed, and drag) are controllable
through AOA manipulation.
6. 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'
D) Aileron reversal and loss of roll control
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 when the critical Mach number
is exceeded.
7. 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
D) Aircraft returns to equilibrium after a disturbance
, 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. Positive
stability would result in damped oscillations.
8. 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
D) Static stability only
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, and neutral stability, where it remains in the new position.
9. 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
D) Decrease lift and increase stall speed
Correct Answer: B
Rationale: Flaps increase the wing's camber, which increases the coefficient of lift and allows
flight at lower airspeeds. They also increase drag, which is beneficial for steep approaches. The
stall speed decreases because the wing can generate more lift at a lower angle of attack.
10. Which factor has the greatest effect on an aircraft's stalling speed?
A) Aircraft weight
B) Wing loading
well detailed exam 2025/2026 graded A+
upgraded !!! Advanced Comprehensive
Examination — 150 Questions with
Detailed Answers and Rationales
SECTION 1: AERODYNAMICS AND PRINCIPLES OF FLIGHT (Questions 1–20)
1. When an aircraft is in steady, unaccelerated flight, the relationship between the four forces
is:
A) Lift equals weight; thrust equals drag
B) Lift is greater than weight; thrust is greater than drag
C) Lift is less than weight; thrust is less than drag
D) Lift equals thrust; weight equals drag
Correct Answer: A
Rationale: In steady, unaccelerated flight, all forces are in equilibrium: lift exactly balances
weight, and thrust exactly balances drag. This fundamental relationship is essential for
understanding performance, stability, and control. Any imbalance results in acceleration or
deceleration.
2. What is the effect on total drag of an aircraft if the airspeed decreases in level flight below
the 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
D) Drag remains constant because total drag is minimized
Correct Answer: C
Rationale: Below the speed for maximum L/D, induced drag increases exponentially as angle of
attack must increase to maintain lift. The wing must generate the same lift at a higher
coefficient of lift, which dramatically increases induced drag. Parasite drag decreases with lower
speed, but the induced drag increase is more significant.
3. What is the condition that may occur when gusts cause a swept-wing airplane to roll in one
direction while yawing in the other?
A) Wingover
B) Mach buffet
C) Dutch roll
D) Spiral instability
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 due to the
inherent yaw-roll coupling characteristics. The oscillation can be uncomfortable and, if severe,
may lead to loss of control.
4. 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
D) Rate will remain constant while radius increases
Correct Answer: A
Rationale: With constant bank angle and increasing airspeed, the rate of turn decreases while
the radius of turn increases. Turn rate is inversely proportional to speed (Rate = g × tan(φ) / V),
,while radius is directly proportional to speed squared (R = V² / (g × tan(φ))) for a given bank
angle.
5. 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
D) Only lift, as airspeed and drag are fixed
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 in the lift
equation L = CL × ½ρV² × S. All three parameters (lift, airspeed, and drag) are controllable
through AOA manipulation.
6. 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'
D) Aileron reversal and loss of roll control
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 when the critical Mach number
is exceeded.
7. 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
D) Aircraft returns to equilibrium after a disturbance
, 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. Positive
stability would result in damped oscillations.
8. 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
D) Static stability only
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, and neutral stability, where it remains in the new position.
9. 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
D) Decrease lift and increase stall speed
Correct Answer: B
Rationale: Flaps increase the wing's camber, which increases the coefficient of lift and allows
flight at lower airspeeds. They also increase drag, which is beneficial for steep approaches. The
stall speed decreases because the wing can generate more lift at a lower angle of attack.
10. Which factor has the greatest effect on an aircraft's stalling speed?
A) Aircraft weight
B) Wing loading
