The mass of an aeroplane does not have any effect on the speed for descent.

The higher the gross mass the greater is the speed for descent.

The higher the average temperature (OAT) the lower is the speed for descent.

The higher the gross mass the lower is the speed for descent.

is the maximum drag speed.

is the point where the Lift to Drag ratio is a maximum.

is the point where Drag coefficient is a minimum

is the point where the Lift to Drag ratio is a minimum.

Extending flaps during the descent results in a smaller Best Glide Angle.

A lower altitude allows for a higher speed while maintaining the same Best Glide Angle.

A higher mass allows for a higher speed while maintaining the same Best Glide Angle

A tailwind component increases the Best Glide Angle for a given speed.

21.8%

 8%

18.5%

30%

1.32VMP

VMP

VMD

1.32VMD

Decrease until transition altitude and remains constant thereafter

Increase until transition altitude and remains constant thereafter.

Increase with altitude.

Decrease with altitude.

Max Range, because this speed corresponds to the maximum lift to drag ratio at the minimum.

Max Endurance, because fuel flow is proportional to thrust at the minimum.

Max Endurance, because fuel flow is proportional to power required.

Max Range, because fuel flow is proportional to lift to drag ratio.

True Airspeed must be low, and the fuel flow must be low.

True Airspeed must be high, and the fuel flow must be low.

True Airspeed must be low, and the fuel flow must be high

True Airspeed must be high, and the fuel flow must be high.

2780 m

2300 m

3 060 m

2580 m

Tailwind.

High mass.

Low mass.

Headwind