PL080 - Principles of Flight PPL(A)
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Flashcards
Which of the following changes is not caused by an increase in the engine thrust?
Wich design feature is not meant to compensate for the slipstream effect?
Which description fits the physical unit called "available power"?
Which description of the physical quantity characterizes the work done?
A plane is flown at an angle of attack, for which the drag coefficient CD is at its minimum. As a result of a slight increase of the angle of attack:
A plane is flown at an angle of attack, for which the drag coefficient CD is at its minimum. As a result of a slight increase of the angle of attack:
The measure of static stability is a derivative of Mx = dM / dx, called the "time derivative of M with respect to variable x". What value of the derivative determines instability?
Eccentricity (decentralization) of the propeller means that:
Eccentricity (decentration)of the propeller:
The engine gyroscopic moment disappears when the following ceases:
The yawing moment that is caused by the aerodynamic force acting on the vertical fin due to an asymmetric airflow behind the propeller is called:
At low airplane speed the highest propeller efficiency is achieved:
The type of spin is mainly influenced by the following factors:
Trim tabs settings; -center of gravity of the airplane; -location and size of the tailplane.
The highest glide ratio in a glide is achieved when the plane is flown (in a calm air) with the following speed:
Power load is called:
Symptom of an airplane in the transition phase is usually:
Interference drag is caused by:
Pulling the yoke causes:
During the stability analysis of plane it is necessary to take into account:
When you yaw the airplane, the powerplant giroscopic moment:
When you pitch the airplane, the powerplant giroskopic moment:
During the approach to landing on an airplane with a variable pitch:
When you perform an engine test before flight the advance ratio is:
When you roll the airplane, the powerplant giroscopic moment:
During steady level flight, the rotating propeller is trying to turn the plane in the direction opposite to the direction of rotation of the blade. That torque is called:
During maneuvers the pilot operates in a feedback loop to respond to the received signals. What are those main signals?
Location of center of pressure on a symmetrical profile, with an increasing angle of attack:
Propeller slip is:
Dynamic stall differes from the static stall, because during the dynamic one:
Stall is a state in which:
Increase of the aircraft pitching moment "Delta M" resulting from the yoke movement is Delta M = Delta L * lH, where:
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:
