POF ATPL Version B

In the event of failure of the Mach trimmer…. the speed must be kept constant. the center of gravity must be moved aft. the Mach number must be limited. the airplane mass must be limited.

Compared to a normal transonic airfoil section a supercritical section has…. a very sharp leading edge. a flatter bottom surface. a more cambered top surface. a flatter top surface.

When air is passing through a shock wave, what happens to the speed of sound?. Decreases. Increases. Is not affected. Decreases and beyond a certain Mach number it starts increasing again.

The max aft position of the center of gravity is amongst others limited by the…. maximum longitudinal stability of the airplane. too small effect of the controls on the airplane. maximum elevator deflection. minimum value of the stick force per g.

Induced drag is created by the…. spanwise flow pattern resulting in the tip vortices. propeller was blowing across the wing. interference of the air stream between wing and fuselage. separation of the boundary layer over the wing.

Static lateral stability will be decreased by: Increasing the size of the vertical tail. Increasing wing sweepback. The use of a low, rather than high, wing mounting. Reducing wing anhedral.

Refer to the figure. All lines refer to the same wing. Line 1 represents an airfoil in clean configurations. Which configuration represents line 3 and is the wing asymmetrical?. Asymmetrical airfoil with leading edge flaps. Asymmetrical airfoil with trailing edge flaps. Symmetrical airfoil with trailing edge flaps. Symmetrical airfoil with leading edge flaps.

Which of these statements about the strength of wing tip vortices are correct or incorrect? I) Assuming no flow separation, the strength of wing tip vortices increases as the angle of attack decreases. II) The strength of wing tip vortices is not affected by aspect ratio decreases. I) correct; II) correct. I) incorrect; II) correct. I) incorrect; II) incorrect. I) correct; II) incorrect.

When is a turn coordinated?. When the longitudinal axis of the airplane at the CG is tangential to the flight path. If no rudder deflection is required during the turn. If no aileron deflection is required during the turn. When only minor elevator pull force is required.

The flaps are an essential part of an aircraft. With their use the aircraft is able to produce (1) ____ lift at (2) ____ speed and with (3) ____ drag. (1) the same; (2) the same; (3) lower. (1) the same; (2) a lower; (3) higher. (1) more; (2) a lower; (3) higher. (1) less; (2) a higher; (3) lower.

The wing platform that gives a constant lift coefficient along the whole area is…. tapered. elliptical. rectangular. swept-back.

When is the Dutch roll tendency the highest?. At low altitudes. At high Mach numbers. When directional stability is stronger than lateral stability. When directional stability is stronger than dynamic stability.

Which of the following devices shows a slotted flap system?. 1,2,3,4. 1,2,3. 1,4. 1 only.

When the air is passing through a shock wave, the density will: Increase. Decrease. Decrease and beyond a certain Mach number start increasing again. Stay constant.

At a given TAS, what effect will an increase in air density have on lift and drag?. Lift and drag will decrease. Lift will decrease and drag will increase. Lift will increase but drag will decrease. Lift and drag will increase.

Assuming ISA conditions and no compressibility effects, if an airplane maintains straight and level flight at the same angle of attack at two different altitudes, the…. TAS is lower at the lower altitude. IAS is higher at the lower altitude. TAS is higher at the lower altitude. IAS is lower at the lower altitude.

Assuming no flow separation and no compressibility effects, the location of the aerodynamic center of an airfoil section…. is independent of the angle of attack. moves forward when the angle of attack is increased. moves backward when the angle of attack increases. is at approximately 50% chord irrespective of angle of attack.

An advantage of locating the engines at the rear of the fuselage, in comparison to a location beneath the wing, is…. a wing which is less sensitive to flutter. less influence on longitudinal control of thrust changes. easier maintenance of the engines. lighter wing construction.

An aerospace company must attach a testing device to the outside of an aircraft. How can the least amount of drag be released?. Using aerodynamic fairing. Placing it underneath the tail section. Placing it on the leading edge of the wing to prevent shock wave formation. Lightening the testing device’s weight.

Assuming ISA conditions and a descent above the tropopause at constant Mach number and airplane mass, the…. IAS decreases. lift coefficient decreases. lift coefficient increases. TAS increases.

Compressibility effects depend on: TAS. Mach number. EAS. IAS.

Which of the following statements about the stall of a straight wing airplane is correct?. The horizontal tail will stall at a higher speed than the wing. The nose down effect is the result of increasing downwash, due to flow separation. Buffeting is the result of flow separation on the tail plane. Just before the stall the airplane will have a nose-down tendency.

Given the following information, for a steady wings level climb of a twin-engine airplane, calculate the all engines climb gradient. Airplane mass: 50 000 kg Lift/Drag ratio: 10 Thrust per engine: 60 000 N Assumed g: 10 m/s². 3.7 %. 11.7 %. 15.7 %. 14 %.

In a straight steady descent, which of the following statements is correct?. Lift is less than weight, load factor is equal to 1. Lift is equal to weight, load factor is less than 1. Lift is less than weight, load factor is less than 1. Lift is equal to weight, load factor is equal to 1.

What characterizes a incipient spin?. Initial rotation has started but not more than 2 turns, and the forces are balanced. Initial rotation has started with more than 2 turns, and the forces are still not completely balanced. Initial rotation has started but not more than 2 turns, and the forces are still not completely balanced. Initial rotation has started with more than 2 turns, and the forces are balanced.

Which of these statements about wing sweepback are correct or incorrect? I) Increasing wing sweepback increases MCRIT. II) Increasing wing sweepback decreases the drag divergence Mach number. I) correct; II) incorrect. I) correct; II) correct. I) incorrect; II) correct. I) incorrect; II) incorrect.

Which of these statements about induced drag are correct or incorrect? I) An elliptical spanwise lift distribution generates less induced drag than a rectangular lift distribution. II) Induced drag decreases with decreasing aspect ratio. I) incorrect; II) incorrect. I) correct; II) incorrect. I) correct; II) correct. I) incorrect; II) correct.

When an airplane enters ground effect…. drag and lift are both reduced. the effective angle of attack is decreased. the lift is increased and the drag is decreased. the induced angle of attack is increased.

The angle of attack of a fixed pitch propeller blade increases when…. velocity and RPM decrease. forward velocity decreases and RPM increases. forward velocity increases and RPM decreases. velocity and RPM increase.

An airplane performs a steady coordinated turn with 20° of bank and at 150 kt TAS. The same airplane with the same bank angle and speed, but at a lower mass will turn with: The same turn radius. A larger turn radius. A higher turn rate. A smaller turn radius.

At which point is the static pressure the lowest on an airfoil?. At the point of maximum camber on the upper surface. On the upper side, where the speed is the highest. At the point where the chord line originates from the leading edge. At the stagnation point.

For a constant flight level and IAS, if the OAT increases, the Mach number will…. remain constant initially, then increase. decrease. increase. remain constant.

With the increasing angle of attack, the stagnation point will move (1) ____ and the point of lowest pressure will move (2) ____. (1) up; (2) aft. (1) down; (2) aft. (1) up; (2) forward. (1) down; (2) forward.

What is true of the L/D ratio in the transonic range?. It does not vary. It decreases. It increases. It is at maximum throughout the range.

Speed of sound…. increases with increasing air density. is proportional to the square root of the absolute temperature. doubles when temperature doubles. decreases with increasing pressure altitude.

Refer to the figure. Assuming no pilot input, the motion of the airplane in the diagram shows: Dynamic longitudinal stability. Dynamic longitudinal instability. Neutral dynamic longitudinal stability. Static longitudinal instability.

Which of the following is the speed for maximum gust?. VD. VB. VC. VA.

State the correct SI unit which is used to express “work”. J. N. Pa. N/m.

Refer to the figure. Select the airfoil that matches the corresponding CL graph. Which augmentation increases your CL while your angle of attack remains the same?. 2,3. 1,2. 3 only. 1 only.

Assuming ISA conditions and a descent below the tropopause at constant Mach number and airplane mass, the: IAS decreases. TAS remains constant. Lift coefficient decreases. Lift coefficient increases.

A negative contribution to the static longitudinal stability of conventional jet transport airplanes is provided by…. the tail. the fuselage. a fixed elevator deflection. a fixed trim position.

What is the effect on an airplane’s characteristics of extending Fowler flaps to their fully extended position?. CD remains constant for a given angle of attack. CLMAX occurs at a higher angle of attack. Wing area and camber increase. Wind area remains constant buy camber increases.

Which of these statements concerning propellers is correct?. A windmilling propeller causes less drag than a feathered propeller. The blade angle of a feathered propeller is approximately 0 degrees. The blade angle of a feathered propeller is approximately 180 degrees. When compared with a non-feathered propeller, a feathered propeller improves the handling of a multi-engine airplane with one engine inoperative.

Induced drag may be reduced by…. a decrease of the aspect ratio. an increase in aspect ratio. an increase in the taper ratio of the wing. the use of a wingtip with a much thinner aerofoil.

Refer to the figure. What kind of horizontal control surface is shown in the figure?. Canard. Elevator. All-flying tail. Frise type control.

Assuming ISA conditions, climbing at a constant Mach number up to the tropopause, the TAS will: Increase. First increase, the decrease. Decrease. Remains constant.