PL080 - Principles of Flight PPL(A)
PPl(A) base
PPl(A) base
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Cartes-fiches
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:
Flap deflection is usually accompanied by
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:
Which property is related to a decrease of airflow in the boundary layer of airofoil?
It is recommended that the change of cruising power to nominal (controllable pitch propeller (CPP) or variable pitch propeller) is made as follows:
It is recommended that the change of take off power to nominal (controllable pitch propeller (CPP) or variable pitch propeller) is made as follows:
An aircraft static margin of a static longitudinal stability this is:
The ability to self-acting return of airplane into equilibrium position after cessation of disturbance is called:
An aerodynamic twist angle of a wing is characterized by:
A geometric twist of a wing is characterized by:
Increasing the unit loading of the planform area causes:
