BASIC AERODYNAMICS

Choose the correct statment regarding wake turbulance. The primary hazard is loss of control because of induced roll. N/A.

If the airplane attitude initailly tends to return to its original position after the elevator control is pressed forward and released, the airplane display. positive static stability. N/A.

Load factor is the lift generated by the wings of an aircraft at any given time. divided by the total weight of the aircraft. N/A.

How much altitude will this airplane lose in 3 statute miles of gliding at an angle of attack of 8°?. 1.320 feet. N/A.

Whis is correct with respect to rate and radius of turn for an airplane flown in a coordinated turn at a constant altitude?. For a specific angle of bank and airspeed, the rate and radius of turn will not vary. N/A.

What does the intersection of the dashed line at point C represents?. Va. N/A.

While maintaining a constant angle of bank and altitude in a coordinated turn, an increase in airspeed will. decrease the rate of turn resulting in no change in load factor. N/A.

A sweptwing airplane with weak static directional stability and increased dihedral cause an increase in. Dutch roll tendency. N/A.

A load factor of 1.2 means the total load on an aircrafts structure is 1.2 times its. gross weight. N/A.

Longitudinal dynamic instability in an airplane can be identified by. pitch oscillations becoming progressively steeper. N/A.

Your flight takes you in the path of a larger aircraft. In order to avoid the vortices you should fly. above the flight path of the larger aircraft. N/A.

If an aircraft with a gross weight of 2000 pounds was subjected to a 60° constant altitude bank, the total load would be. 4000 pounds. N/A.

Which is true regarding the force acting on an aircraft in a stedy-state descent? The sum of all. forward forces is equal to the sum of all rearward forces. N/A.

The angle of attack of a wing directly controls the. distribution of pressure acting on the wing. N/A.

In a rapid recovery from a dive, the effects of load factor would cause the stall speed to. increase. N/A.

A rectangular wing, as compared to other wing planforms, has a tendency to stall first at the. wing root, whith the stall progression toward the wing tip. N/A.

Lift on a wing is most properly defined as the. force acting perpendicular to the relative wind. N/A.

To produce the same lift while in ground effect as when out of ground effect, the airplane requires. a lower angle of attack. N/A.

What increase in load factor would take place if the angle of bank increased from 60° to 80°?. 4 Gs. N/A.

When transitioning from straight-and-level flight to a constant airspeed climb, the angle of attack and lift. are momentarily increased and lift returns to a stedy state during climb. N/A.

While executing a 60 degree level turn, your aircraft is at a load factor of 2.0. What does this mean?. The total load on the aircraft s structure is two times its weight. N/A.

The L/D ratio at a 2° angle of attack is approximately the same as the L/D ratio for a. 16.5° angle of attack. N/A.

Longitudinal stability involves the motion of the airplane controlled by its. elevator. N/A.

If the same angle of attack is maintained in ground effect as when out of ground effect, lift will. increased, and induced drag will decrease. N/A.

As aispeed decrases in level flight below that speed for maximum lift/drag ratio, total drag of an airplane. increases because of increased induced drag. N/A.

Which is true regarding the force of lift in steady, unaccelerated flight?. There is a corresponding indicated airspeed required for every angle of attack to generate sufficient lift to maintain altitude. N/A.

The need to slow an aircraft below V(A) is brought about by the following weather phenomenon: Turbulance which cause an increase in stall speed. N/A.

The ratio between the total airload imposed on the wing and the gross weight of an aircraft in flight is known as. load factor and directly affects stall speed. N/A.

An aircraft airfoil is designed to produce lift resulting from a difference in the. higher air pressure below the airfoil s surface and lower air pressure above the airfloil s surface. N/A.

When landing behind a large aircraft, which procedure should be followed for vortex avoidance?. Stay above its final approach flightpath all the way to touchdown. N/A.

Why is it necessary to increase back elevator pressure to maintain altitude during a turn? To compensate for the. loss of the vertical component of lift. N/A.

Which statement is true, regarding the opposing forces acting on an airplane in steady state level flight?. These forces are equal. N/A.

If an airplane category is listed as utility, it would mean that this airplane could be operated in which of the following maneuvers?. Limited acrobatics, including spins (if approved). N/A.

Select the correct statment regarding stall speeds. Power-on stalls occur at lower airspeeds in shollower banks. N/A.

If airspeed is increased during a level turn, what action would be necessary to maintain altitude? The angle of attack. must be decreased or angle of bank increased. N/A.

If an airplane is loaded to the rear of its CG range, it will tend to be unstable about its. lateral axis. N/A.

At the airspeed represented by point A, in steady flight, the airplane will. have its maximum L/D ratio. N/A.

On a wing, the force of lift acts perpendicular to and the force of drag acts paralles to the. flightpath. N/A.

Recovery from stall in any airplane becomes more difficult when its. center of gravity moves aft. N/A.

An airplane will stall at the same. angle of attack regardless of the attitude with relation to the horizon. N/A.

As the angle of bank is increased, the vertical component of lift. decreases and the horizontal component of lift increases. N/A.

What is the speed of an airplane under a load factor of 2.5 Gs if the unaccelerated stall speed is 60 knots?. 96knots. N/A.

Which is true regarding the use of flaps during level turns?. The raising of flaps increases the stall speed. N/A.

A propeller rotating clockwise as seen from the rear, creates a spiraling slipstream. The spiraling slipstream, along with torque effect, tends to rotate the airplane to the. left around the vertical axis, and to the left around the longitudibal axis. N/A.

Select the correct statement regarding stall speeds. The airplane will stall. 10 knots higher in a power-on 60° bank with gear and flaps up than with gear and flaps down. N/A.

In small airplanes, normal recovery from spins may become difficult if the. CG is too far rearward and rotation is around the CG. N/A.

To maintain altitude during a turn, the angle of attack must be increased to compensate for the decrease in the. vertical component of lift. N/A.

If the airspeed is decreased from 98 knots to 85 knots during a coordinated level 45 degree banked turn, the load factor will. remain the same, but the radius of turn will decrease. N/A.

To generate the same amount of lift as altitude is increased, an airplane must be flown at. a higher true airspeed for any given angle of attack. N/A.

The horizontal dashed line from point C to point E represents the. positive limit load factor. N/A.

While holding the angle of bank constant in a level turn, if the rate of turn is varied the load factor would. remain constant regarless of air density and the result lift vector. N/A.

In theory, if the airspeed of an aircraft in level flight is cut in half while in level flight, parasite drag will become. one fourth as much. N/A.

Airplane wing loading during a level coordinated turn in smooth air depends upon the. angle of bank. N/A.

Which statement is true relative to changing angle of attack?. An increase in angle of attack will increase drag. N/A.

During a takeoff made behind a departing large jet airplane, the pilot can minimize the hazard of wingtip vortices by. being airborne prior to reaching the jets flightpath until able to tuen clear of tis wake. N/A.

What is the best indicator to the pilot of the load factor on the airplane?. How firmly the pilot is pressed into the seat during maneuvers. N/A.

To increase the rate of turn and at the same time decrease the radius, a pilot should. increase the bank and decrese airspeed. N/A.

The angle of attack at which a wing stalls remains constant regardless of. weight, dynamic pressure, bank angle, or pitch attitude. N/A.

Which maximum range factor decreases as weight decrases?. Airspeed. N/A.

An airplane leaving ground effect will. experience an increase in induced drag and require more thrust. N/A.

One of the main functions of flaps during the approach and landing is to. provide the same amount of lift at a slower airspeed. N/A.

What changes in airplane longitudinal control must be made to maintain altitude while the airspeed is being decreased?. Increase the angle of attack to compensate for the decreasing lift. N/A.

What performance is characteristic of flight at maximum lift/drag ratio in a propeller driven airplane? maximum. range and maximum distance glide. N/A.

If the airspeed is increased from 90 knots to 135 knots during a level 60° banked turn, the load factor will. remain the same but the radius of turn will increase. N/A.

To maintain a standard rate turn as the airspeed increases, the bank angle of the aircraft will need to. increase. N/A.

To avoid possible wake turbulance from a large jet aircraft that has justlanded prior to your takeoff, at which point on the runway should you plan to become airborne?. Past the point where the jet touched down. N/A.

The stalling speed of an airplane is most affected by. variation in airplane loading. N/A.

At an airspeed represented by point B, in stedy flight, the pilot can expect to obtain the airplanes maximum. glide range. N/A.

To hold and airplane in level flight at airspeed from very slow to very fast, a pilot must coordinate thrust and. angle of attack. N/A.

If an airplane glides at an angle of attack of 10°, how much altitude will it lose in 1 mile?. 480 feet. N/A.

The vertical speed line from point E to point F is represented on the aispeed indicator by the. upper limit of the yellow arc. N/A.

If the airplane attitude remains in a new position after the elevator control is pressed forward and released, the airplane displays. neutral longitudinal static stability. N/A.

Stall speed is affected by. weight, load factor, and power. N/A.

Which is true respect to vortex circulation in the wake turbulance generated by an aircraft?. The vortex strenght is greatest when the generating aircraft is heavy, clean, and slow. N/A.

In theory, if the angle of attack and other factors remains constant and the airspeed is doubled, the lift produced at the higher speed will be. four times greater than at the lower speed. N/A.

What is the stall speed of an airplane under a load factor of 2Gs if the unaccelerated stall speed is 60 knots?. 84 knots. N/A.

If the airspeed is increased from 89knots to 98 knots during coordinated level 45° banked tuen, the load factor will. remains the same, but the radius of turn will increase. N/A.

By changing the angle of attack of a wing, the pilot can control the airplanes. lift, airspeed and drag. N/A.

In theory, if the airspeed of an airplane is double while in level flight, parasite drag will become. four times greater. N/A.

An aircraft wing is designed to produce lift resulting from a difference in the. higher air pressure below the wings surface and lower air pressure above the wings surface. N/A.