Essay John Locke
When comparing Vx to Vy:
a) Vy will always be greater than or equal to Vx <-- Correct
b) Vy will always be greater than Vx
Climb Performance
A headwind component increasing with altitude, as compared to zero wind condition (assuming IAS is constant):
a) has no effect on rate of climb <-- Correct
b) improves angle and rate of climb
c) does not have any effect on the angle of flight path during climb
d) decreases angle and rate of climb
With increasing altitude, the rate of climb: "decreases because power available decreases and power required increases"
The rate of climb:
a) Is approximately climb gradient times true airspeed divided by 100 <-- Correct
The climb gradient is defined as the ratio of:
a) The increase of altitude to horizontal air distance expressed as a percentage <-- Correct
b) The increase of altitude to distance over ground expressed as a percentage
c) True airspeed to rate of climb
d) Rate of climb to true airspeed
Equations below expresses approximately the un-accelerated percentage climb gradient for small climb angles:
Climb Gradient = [(Thrust - Drag)/Weight] x 100
Assuming that the required lift exists, which forces determine an aeroplane's angle of climb? "Weight, drag and thrust"
For a given aircraft mass, the climb gradient: "decreases with increasing flap angle and increasing temperature"
In un-accelerated climb thrust equals drag plus the downhill component of the gross weight in the flight path direction.
What will happen to VX and VY if the landing gear is extended? "VX and VY decrease"
Increase in the profile drag will shift the drag curve to the left.
If the aircraft mass increases, how does the (i) rate of climb, and (ii) rate of climb speed change?
a) decrease; increase
Rate of Climb = (Power Available - Power Required) / Weight
Climb Performance
Other factors remaining constant, how does increasing altitude affect Vx and
a) Vy will always be greater than or equal to Vx <-- Correct
b) Vy will always be greater than Vx
Climb Performance
A headwind component increasing with altitude, as compared to zero wind condition (assuming IAS is constant):
a) has no effect on rate of climb <-- Correct
b) improves angle and rate of climb
c) does not have any effect on the angle of flight path during climb
d) decreases angle and rate of climb
With increasing altitude, the rate of climb: "decreases because power available decreases and power required increases"
The rate of climb:
a) Is approximately climb gradient times true airspeed divided by 100 <-- Correct
The climb gradient is defined as the ratio of:
a) The increase of altitude to horizontal air distance expressed as a percentage <-- Correct
b) The increase of altitude to distance over ground expressed as a percentage
c) True airspeed to rate of climb
d) Rate of climb to true airspeed
Equations below expresses approximately the un-accelerated percentage climb gradient for small climb angles:
Climb Gradient = [(Thrust - Drag)/Weight] x 100
Assuming that the required lift exists, which forces determine an aeroplane's angle of climb? "Weight, drag and thrust"
For a given aircraft mass, the climb gradient: "decreases with increasing flap angle and increasing temperature"
In un-accelerated climb thrust equals drag plus the downhill component of the gross weight in the flight path direction.
What will happen to VX and VY if the landing gear is extended? "VX and VY decrease"
Increase in the profile drag will shift the drag curve to the left.
If the aircraft mass increases, how does the (i) rate of climb, and (ii) rate of climb speed change?
a) decrease; increase
Rate of Climb = (Power Available - Power Required) / Weight
Climb Performance
Other factors remaining constant, how does increasing altitude affect Vx and