PL080 - Principles of Flight PPL(A)

When considering the stability of the airplane in an Cartesian (XYZ) coordinate system, we assume that all three axes pass through:

The aircraft flies horizontally at economic speed. To establish horizontal fly with minimal speed (Vs) we should to do: 

An airplane during stall configuration is:

The plane in the spin phase is characterized by: 

Aircrafts used in general aviation are usually constructed that:

The geometric Pitch of the propeller is

Actual pitch propeller: 

The propeller efficiency is equal zero only when: 

The state of balance, when the mass is usually existing and to which always returns after being displaced from a given equilibrium position is named:

Dynamic lateral stability mainly depends from: 

Dynamic longitudinal stability mainly depends from: 

Dynamic stability is:

Static directional stability depends from:

Static longitudinal stability mainly depends from:

Static lateral stability mainly depends from: 

Static stability is:

A controllability is: 

The ratio of work done by the propeller to the power consumed by a propeller from the engine is called:

The quatient of airspeed TAS to Revolution per Minute (RPM) of the propeller blade cross-section is called: 

Propeller of aircraft, in order to maximize of efficiency should to be:

In order to recovery of the plane from autorotation (spin) it is necesary: 

Apply roll ailerons into the opposite direction of roll, push down the stick. 

In order to recovery of the plane from the spin in following sequence: 

In order to reduce the inclination of the plane:

In order to reduce the inclination of the plane:

In order to reduce the inclination of the plane:

In order to reduce the inclination of the plane:

In order to increase the inclination of the plane:

In order to increase the inclination of the plane:

In order to increase the inclination of the plane:

To increase up the pitch of the plane we should to do: 

In which document are there information about the performance of the aircraft (helicopter, aircraft, etc.)? 

In case when the propeller angle of attack(AoA) is equals the blade angle of the propeller it is true that: 

In an quiet air, the glide-angle with off an engine during incease of aicraft load:

In a fixed straight horizontal flight the load factor of plane is: 

 In the fixed turn of plane the load factor "n" is: 

As a achieving result of the glide-angle: 

As a result of a slight increase of the angle of attack (AoA) over glide-angle: 

As a result of a slightly increase the angle of attack (AoA) over glide-angle:

Aileron deflection to the left during the stall will cause: