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Principle of Flight - PPL(A) English - Private Pilot License (Aircraft)
Principle of Flight - PPL(A) English - Private Pilot License (Aircraft)
Test 10 domande Principle of Flight, tempo libero
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Nuovo Test!
1 - Stability around which axis is mainly influenced by the center of gravity's longitudinal position?
Vertical axis
Longitudinal axis
Gravity axis
Lateral axis
2 - Stabilization around the lateral axis during cruise is achieved by the...
Horizontal stabilizer.
Airlerons
Wing flaps.
Vertical rudder.
3 - Which statement about the airflow around an aerofoil is correct if the angle of attack decreases?
The center of pressure moves aft
The stagnation point remains constant
The stagnation point moves down
The center of pressure moves forward
4 - What effects typically result from propeller icing?
Reduced power output, decreasing RPM
Increased power output, decreasing RPM.
Increased power output, increasing RPM.
Reduced power output, increasing RPM.
5 - Bernoulli's equation for frictionless, incompressible gases states that...
Static pressure = total pressure + dynamic pressure
Total pressure = dynamic pressure - static pressure
Dynamic pressure = total pressure + static pressure.
Total pressure = dynamic pressure + static pressure.
6 - Which constructive feature has the purpose to reduce stearing forces?
T-tail
Vortex generators
Differential aileron deflection
Aerodynamic rudder balance
7 - During a straight and steady climb, which force acts addionally, and in the same direction as the drag force, resulting in more power required for climb than for horizontal flight?
A component of the weight force along the rearward flight path
The vertical component of the weight force
A component of the thrust along the rearward flightpath.
A component of the lift force along the forward flightpath.
8 - Number 3 in the drawing corresponds to the... See figure (PFA-010) (1,00 P.) Siehe Anlage 1
Chord
Thickness
Camber line
Chord line.
9 - Which point on the aerofoil is represented by number 3? See figure (PFA-009) (1,00 P.) Siehe Anlage 2
Separation point
Center of pressure
Stagnation point
Transition point
10 - The drag coefficient...
Increases with increasing airspeed.
Is proportional to the lift coefficient.
Cannot be lower than a non-negative, minimal value.
May range from zero to an infinite positive value
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