An aerofoil when placed in a flow will (normally) cause said flow to accelerate over the aerofoil and decelerate below it.

This will cause a pressure differential between the upper and lower surface of the aerofoil, and the resultant force will be applied at the center of pressure.

The weight of an aircraft is applied at the CG. The lift at the CP. The relative position between these 2 points determines the stability of the aircraft. For an Aircraft with a tail surface, a CG in front of the CP constitutes a stable system, while a CG behind the CP an unstable system.

It's vertical velocity of the aircraft usually expressed in feet per minute.

35 ft

For Reference:

• 50ft for Class B or A (<15° AoB at take-off or normal landings)

• 35ft for Class A (dry take-off or steep approach)

• 15ft for Class A (wet take-off)

Government sources.

L = 1/2 * rho * Cl * A * V^2

The distance from the datum to the point at which the weight of a component acts.

Advection fog occurs when moist air passes over a cool surface by advection (wind) and is cooled.

It is common as a warm front passes over an area with significant snowpack, but it is most common at sea when tropical air encounters cooler waters, including areas of cold water upwelling, such as along the coast of California.

A moving stabilator allows for wider operating range of the control surface, which is of great importance in aircraft with a large range of operating speeds.

Compared to a fixed horizontal stabilizer, when trimmed, the moving stabilitor will produce less drag, reducing fuel consumption.

Center of pressure moves forward when approaching a stall.