Theorique PPL Flashcards
(99 cards)
An aeroplane’s wing loading during a level coordinated turn in smooth air depends upon the :
- Angle of bank
- True airspeed
- Angle of attack
- Rate of turn
Angle of attack
Which is true with respect to changing the angle of attack?
- An increase in angle of attack will increase drag
- An increase in angle of attack will decrease in drag
- A decrease in angle of attack will increase pressure bellow the wing and decrease drag
- An increase in angle of attack will decrease pressure below the wing and increase drag
An increase in angle of attack will increase drag
During a level turn while maintaining a constant angle of bank, varying the rate of turn by changing the airspeed the load factor would :
- Vary the depending upon the resultant lift vector
- Vary depending upon speed
- Remain constant
- Do none of the above
Remain constant
During flight with a zero degree of angle of attack the pressure along the upper surface of an asymmetrical wing would be:
- Less than the atmospheric pressure
- Greater than the atmospheric pressure
- Equal to the atmospheric pressure
- None of the above
Less than the atmospherical pressure
For a given angle of bank in an aeroplane, the load factor imposed in a coordinated constant-altitude turn is :
- Greater than in straight and level flight, and the stall speed increases.
- Greater than in straight and level flight, and the stall speed decreases
- Varied with the rate of turn
- None of the above
Greater than in straight and level flight, and the stall speed increases
The action necessary to make an aeroplane turn is to :
- Provide a centripetal force that overcomes the weight by banking the wing
- Produce horizontal component of lift, known as centripetal force, by banking the wing
- Produce horizontal component of lift, known as centrifugal force by banking the wing
- Provide a centrifugal force that overcomes the weight by banking the wing
Produce horizontal component of lift, known as centripetal force, by banking the wing
The relationship of the forces acting on an aircraft in a constant-power constant airspeed descent means that the :
- Weight is greater than lift
- Thrust is equal to drag and lift is less than weight
- Thrust is greater than drag and weight is greater than lift
- Sum of the horizontal forces and vertical forces are zero
Sum of the horizontal forces and vertical forces are zero
Regarding the forces acting on an aeroplane in a steady state climb that :
- The sum of all upward forces is equal to the sum of all downward forces
- The sum of all upward forces is more than the sum of all downward forces
- The sum of all forward forces is greater than the sum of all rearward forces
- None of the above is correct
The sum of all upward forces is equal to the sum of all downward forces
The critical angle of attack at which a given aeroplane wing stalls is dependent on the :
- Gross weight, design of the wing and critical surface contamination
- Design of the wing and critical surface contamination
- Attitude and true airspeed
- Critical surface contamination and gross weight
Design of the wing and critical surface contamination
When considering the forces acting upon an aeroplane in straight and level flight at a constant airspeed, which is correct?
- Lift always acts perpendicular to the longitudinal axis of the wing and is greater than weight
- Weight always acts vertically toward the center of the Earth
- Thrust always acts forward parallel to the relative wind and is greater than drag
- None of the above
Weight always acts vertically toward the center of the Earth
An aeroplane has greater longitudinal stability when the :
- Wings have a high angle of incidence
- Wings have a high dihedral angle
- Center of pressure is forward the center of gravity
- Center of gravity is well forward of the center of pressure
Center of gravity is well forward of the center of pressure
Considering a flight in turbulent conditions, the effect that a decrease in the aeroplane’s gross weight will have is that :
- A lesser angle of attack will be required to stall the wing
- A greater angler of attack will be required to stall the wing
- The manoeuvring speed will be higher
- The manoeuvring speed will be lower
The manoeuvring speed will be lower
Describe dynamic longitudinal stability :
- Motion about the longitudinal axis
- Motion about the lateral axis
- Motion about the vertical axis
- All of the above
Motion about the lateral axis
In the northern hemisphere the magnetic compass will initially indicate a turn toward the east if the aircraft :
Enters a left turn from a northerly heading
Accelerates while on a northerly heading
Decelerates while on a southerly heading
Enters a right turn from a northerly heading
Enters a left turn from a northerly heading
The angular difference between the true North Pole and the magnetic North Pole is called
Variation
Magnetic field
Agonic difference
Deviation
Variation
What important limiting speed is not marked on the airspeed indicator?
Maximum structural cruising speed
Maximum flaps extended speed
Never exceed speed
Manoeuvring speed
Manoeuvring speed
Calibrated airspeed (CAS) is the :
Indicated airspeed corrected for installation and instrument errors
Actual speed of an aircraft over the ground
Airspeed corrected for altitude and nonstandard temperature
Airspeed read directly from the airspeed indicator
Indicated airspeed corrected for installation and instrument errors.
True airspeed (TAS) is the :
Actual speed of an aircraft over the ground
Airspeed read directly from the airspeed indicator
Indicated airspeed corrected for installation and instrument errors
Calibrated airspeed corrected for altitude and nonstandard temperature
Calibrated airspeed corrected for altitude and nonstandard temperature
A common cause of a surface-based inversion is the :
Passage of a warm air mass over a cool surface
Rapid lifting of warm moist air as it moves up a mountain slope
Lifting of air along a cold front
Radiation cooling from the surface on clear nights
Radiation cooling from the surface on clear nights
Temperature inversion exists when the temperature of the air increases with an increase in altitude. True or False?
True
Cloud, fog, or dew will always form when :
Smoke is present
Water vapor is present
Water vapor condenses
Relative humidity reaches 100%
Water vapor condenses
Density altitude can be obtained by dialing in 29.92 in Hg on the altimeter sub-scale. True or False?
False
The density altitude is the air density given as a height above mean sea level.
Frost will form when the surface of the aircraft is at or below the dew point of the adjacent air and when :
The dew point temperature is colder than freezing
Dew is on the aircraft
The relative humidity is high
Light rain is falling
The dew point temperature is colder than freezing
If a flight is made from an area of high pressure into an area of lower pressure without the altimeter setting being adjusted, the altimeter will indicate :
Lower than the actual altitude above sea level.
The actual altitude above the sea level.
Higher than the actual altitude above sea level.
None of the above.
Higher than the actual altitude above the sea level.