Commercial – Chapter 1 – Airplanes and Aerodynamics

One of the main functions of flaps during the approach and landing is to

Which is true regarding the use of flaps during level turns?

Some aircraft are fitted with wing spoilers to decrease

An aircraft airfoil is designed to produce lift resulting from a difference in the

A rectangular wing, as compared to other wing planforms, has a tendency to stall first at the

The angle of attack of a wing directly controls the

Frost covering the upper surface of an airplane wing usually will cause

By changing the angle of attack of a wing, the pilot can control the airplane’s

When a pilot increases the angle of attack on a symmetrical airfoil, the center of pressure  will

The critical angle of attack is exceeded when

The angle of attack at which a wing stalls remains constant regardless of

The design maneuvering speed is

The need to slow an aircraft below Va is brought about by the following weather phenomenon.

Stall speed is affected by

An airplane will stall at the same

Refer to figure 2 below. Select the correct statement regarding stall speeds.

Refer to figure 2 below. Select the correct statement regarding stall speeds. The airplane will stall

A stall will occur

Refer to figure 3 below. Use the diagram to determine the critical angle of attack

In a rapid recovery from a dive, the effects of load factor would cause the stall speed to

The stalling speed of an airplane is most affected by

Recovery from a stall in any airplane becomes more difficult when its

A left side slip is used to counteract a crosswind drift during the final approach for landing. An over-the­ top spin would most likely occur if the controls were used in which of the following ways? Holding the stick

In small airplanes, normal recovery from spins may become difficult if the

Which statement is true relative to changing angle of attack?

To generate the same amount of lift as altitude is increased, an airplane must be flown at

A pilot who intends to maintain level flight must coordinate the angle of attack and

As the angle of bank is increased, the vertical component of lift

Which is true regarding the forces acting on an aircraft in a steady-state descent? The sum of all

During the transition from straight-and-level flight to a climb, the angle of attack is increased and lift

Which is true regarding the force of lift in steady, unaccelerated flight?

What changes in airplane longitudinal control must be made to maintain altitude while the airspeed is being decreased?

In theory, if the airspeed of an airplane is doubled while in level flight, parasite drag will  become

As airspeed decreases in level flight below that speed for maximum lift/drag ratio, total drag of an airplane

If airspeed remains constant, but the air density increases, what will be the effect on both lift and drag?

Refer to figure 1 below. At an airspeed represented by point B, in steady flight, the pilot can expect to obtain the airplane’s  maximum

Refer to figure 1 below.  At the airspeed represented by point A, in steady flight, the airplane will

What performance is characteristic of flight at maximum lift/drag ratio in a propeller-driven airplane? Maximum

In theory, if the angle of attack and other factors remain constant and the airspeed is doubled, the lift produced at the  higher speed will be

An aircraft wing is designed to produce lift resulting from a difference in the

To hold an airplane in level flight at airspeeds from very slow to very fast, a pilot must coordinate thrust and

Lift on a wing is most properly defined as the

In theory, if the airspeed of an aircraft is cut in half while in level flight, parasite drag will become

Refer to figure 3 below. If an airplane glides at an angle of attack of 10 degrees, how much altitude will it lose in 1 mile?

Refer to figure 3 below. How much altitude will this airplane lose in 3 statute miles of gliding at an angle of attack of 8 degrees?

Refer to figure 3 below. The L/D ratio at a 2 degree angle of attack is approximately the same as the L/D ratio for a

On a wing, the force of lift acts perpendicular to and the force of drag acts parallel to the

Which statement is true regarding the opposing forces acting on an airplane in steady-state level flight?

Both lift and drag would be increased when which of these devices are extended?

Refer to figure 3A below. As you are flying with a headwind from the coastline inland toward your destination airport, your aircraft has engine failure. You would expect your glide path to be

Refer to figure 3A below. At an altitude of 2,000 feet AGL, how far would you expect to glide?

An airplane leaving ground effect will

To produce the same lift while in ground effect as when out of ground effect, the airplane requires

If the same angle of attack is maintained in ground effect as when out of ground effect, lift will

Longitudinal stability involves the motion of the airplane controlled by its

Longitudinal dynamic instability in an airplane can be identified by

If the airplane attitude remains in a new position after the elevator control is pressed forward and released, the airplane displays

If the airplane attitude initially tends to return to its original position after the elevator control is pressed forward and released, the airplane displays

If an airplane is loaded to the rear of its CG range, it will tend to be unstable about its

If airspeed is increased during a level turn, what action would be necessary to maintain altitude? The angle of attack

If a standard rate turn is maintained, how long would it take to turn 360 degrees?

While holding the angle of bank constant in a level turn, if the rate of turn is varied the load factor would

Which is correct with respect to rate and radius of turn for an airplane flown in a coordinated turn at a constant altitude?

To increase the rate of turn and at the same time decrease the radius, a pilot should

While maintaining a constant angle of bank and altitude in a coordinated turn, an increase in airspeed will

Why is it necessary to increase back elevator pressure to maintain altitude during a turn? To compensate for the

To maintain altitude during a turn, the angle of attack must be increased to compensate for the decrease in the

The ratio between the total airload imposed on the wing and the gross weight of an aircraft in flight is known as

Load factor is the lift generated by the wings of an aircraft at any given time.

For a given angle of bank, in any airplane, the load factor imposed in a coordinated constant-altitude turn

Airplane wing loading during a level coordinated turn in smooth air depends upon the

The load factor for an airplane in a 60 degree banked turn is

A load factor of 1.2 means the total load on an aircraft’s structure is 1.2 times its

If an aircraft with a gross weight of 2,000 pounds was subjected to a 60° constant-altitude bank, the total load would be

If the airspeed is increased from 90 knots to 135 knots during a level 60° banked turn, the load factor will

If the airspeed is decreased from 98 knots to 85 knots during a coordinated level 45° banked turn, the load factor will

Refer to figure 4 below. What increase in load factor would take lace if the angle of bank were increased from 60 degrees to 80 degrees.

Refer to figure 4 below. What is the stall speed of an airplane under a load factor of 2.5 Gs if the unaccelerated  stall speed is 60  knots?

Refer to figure 4 below. What is the stall speed of an airplane under a load factor of 2 Gs if the unaccelerated  stall speed is 60 knots?

Which factor below is the best indication of positive or negative Gs in an aircraft?

Baggage weighing 90 pounds is placed in a no ma! category airplane’s baggage compartment, which 1s placarded at 100 pounds. If this airplane is subjected to a positive load factor of 3.5 Gs, the total load of the baggage would be

Which of the following would best indicate to the pilot that the load factor placed on the airframe has been increased?

The ratio of an airplane’s true airspeed to the speed of sound in the same atmospheric conditions is

Transonic airflow typically occurs in airplane speed regimes between Mach

Acceleration past critical Mach speed may cause compressibility issues such as

If the airspeed is increased from 89 knots to 98 knots during a coordinated level 45 degree banked turn, the load factor will

Accelerating past critical Mach may result in the onset of compressibility effects such as