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As we could observe in aviation power curves post, there are some points where the Pa=Pr corresponds to a null Rate of climb. That is why the rate of climb curve has a shape of a hill. The top corresponds to the maximum Rate of climb.

The way to calculate the Vx and Vy is the result of drawing the R/c curve related to its speed. The top of the curve is VY and the tangent from the origin to R/c curve is Vx.

**Weight:** The heavier the plane is, the less angle and rate of climb it has. In the post climb aircraft performances we can see that in each of the formulas the weight is dividing. So the new Rate of climb curve is smaller.

If we draw the graphic of the rate of climb curve related to its speed, we notice that Vx and Vy increases. Another way to see that is: if the weight increases we required more lift,and for getting more lift the speed must increase.

**Flap Setting**: the higher flap setting, the less rate and angle of climb, due to the power required increases. On the other hand with higher wing surface the speed we need to get the same amount of lift decreases that´s why the rate of climb curve related to its speed moves to the left, resulting in an Vy and Vx decreases.

**Altitude:** As we know the higher we fly, the higher density altitude we have. That leads on an increase of power required, decrease of power available, and increase of True Air Speed (TAS, this concept we will see it in a principles of flight post). That´s why the rate of climb related to its speed curve moves lo the right, and Vx and Vy increases.

**Load Factor:** The load factor is also known as a G force. When we make a turn our weight increases due to the G force, so the effect is similar to the increase of weight shown above.

**Wind:** The wind does not have any effect on the power curves, so the Angle and Rate of climb should be the same. But unfortunately this statement is only true with the rate of climb.

If the Angle of climb is the path between ground and the trajectory of the plane. As the rate of climb does not change and the Ground speed changes. That leads on a change of the angle of climb (see the picture bellow).

All planes have a maximun altitude they can climb, that altitude it is the Cealing of an aircraft.

**Absolute Ceiling:** ocurrs when we do not have this excess of power . So Vx=Vy

**Service Ceiling :** Altitude where the aircraft can mantain a rate of climb of 100 feet/min.

**Cruise Ceiling:** Altitud where the aircraft can mantain a rate of climb of 300 feet/min

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