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PL080 - Principles of Flight PPL(A)

PPl(A) base

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Flashcards	370
Language	English
Category	Technology
Level	Other
Created / Updated	28.04.2022 / 11.05.2022
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Flap deflection is usually accompanied by

Increase of the Cz, increase of the Cx and decrease of the L/D ratio.

Increase of the Cz, increase of the Cx and increase of the L/D ratio.

Increase of the Cz, increase of the Cx not changed of the L/D ratio.

Displacement of the neutral balance center of the plane.

A graph the allegiance of the CD as a function of the CL Cl = f (Cx) performed on the basis of measurements during a flight, is called:

The Drag Polar of the aircraft.

The speed polar of the aircraft.

The wing polar.

The airfoil polar.

Which property is related to a decrease of airflow in the boundary layer of airofoil?

The viscous of the air.

The air density.

The stagnacy of the air.

The air ballance.

It is recommended that the change of cruising power to nominal (controllable pitch propeller (CPP) or variable pitch propeller) is made as follows:

First increasing of a propeller pitch and then increase of the throttle.

First reducing of the throttle then increasing of the propeller pitch.

Increasing of the propeller pitch, and then reducing of the throttle.

Increasing throttle and then decrease of the propeller pitch.

It is recommended that the change of take off power to nominal (controllable pitch propeller (CPP) or variable pitch propeller) is made as follows:

First reducing of the throttle next increasing the propeller pitch.

First increasing the propeller pitch next reducing the throttle.

Increase throttle next decrease the propeller pitch.

Reducing of propeller pitch next increase the throttle.

An aircraft static margin of a static longitudinal stability this is:

The distance between the Center of Gravity of the aircraft and the Neutral Point.

The distance between the Center of Gravity of the airplane and aerodynamic center (AC).

The distance between the Neutral balance center and the aerodynamic center (AC).

The distance between the aerodynamic center of control surface and the aerodynamice center of the wing.

The ability to self-acting return of airplane into equilibrium position after cessation of disturbance is called:

The Dynamic Stability.

The static stability.

The Static Controllability.

The Dynamic controllability.

An aerodynamic twist angle of a wing is characterized by:

On the tips od the wings there are airfoils, where the separated airflow leaving the wing for Absolute Angle of Attack (Absolute AoA) is less intense.

Tips of wings are twistet down when speed is equal to 0.

Tips of wings are curved up during in flight.

A geometric twist of a wing is characterized by:

Geometric chord profiles in subsequent sections do not lie in one plane.

Tips of wings are twistet down when speed is equal to 0.

Tips of wings are curved up during in flight.

On the tips od the wings there are airfoils, where the separated airflow leaving the wing for Absolute Angle of Attack (Absolute AoA) is less intense.

Increasing the unit loading of the planform area causes:

Take off and landing distance extending- increase of minimal speed (Vs)- decrease in maximal climbing rate(RoCmax).

Take off and landing distance - increse in minimal speed(Vs) - decrease in maximal climbing rate(RoCmax).

Take off and landing distance extending - decrease of minimal speed(Vs) - decrease in maximal climbing rate(RoCmax).

Take off and landing distance extending - increase in minimal speed(Vs) - increase in maximal climbing rate(RoCmax).