Flaps and Slats in Aircraft

Flaps are hinged surfaces mounted on the ______ edges of the wings of a fixed-wing aircraft.

Slats are aerodynamic surfaces on the ______ edge of the wings of fixed-wing aircraft.

The general airplane lift equation is: L = ______ * V * S * CL.

Increasing the area (S) and lift coefficient (CL) allows for the production of a certain ______ of lift at a lower airspeed (V).

Flaps shorten ______ and landing distances.

Slats are used while ______ or performing manoeuvers which take the aircraft close to the stall.

Slats are like flaps only but extended over the ______ edge of the wings.

The Slat lies flush with the wing ______ edge until reduced aerodynamic forces allow it to extend by way of aerodynamics when needed.

A ______ is a reduction in the lift coefficient generated by foil as angle of attack increases.

The critical angle of attack is typically about ______ degrees.

A ______ does not mean that the engine(s) have stopped working, or that the aircraft has stopped moving.

The critical angle of attack is dependent upon the profile of the ______, its platform, its aspect ratio, and other factors.

Flow separation begins to occur at small angles of attack with attached airflow over the ______ still dominant.

At the critical angle of attack, separated flow is so dominant that further increases in angle of attack produce less ______ and vastly more drag.

The angle at which this occurs is called the critical angle of ______.

Stalls in fixed-wing flight are often experienced as a sudden reduction in ______ as the pilot increases angle of attack.

A fixed-wing aircraft during a stall may experience ______ or a change in attitude.

Most aircraft are designed to have a gradual ______ characteristics that will warn the pilot and give the pilot time to react.

The critical angle of attack in steady straight and level flight can be attained only at low ______.

Stalls depend only on ______ of attack, not airspeed, however, because a correlation with airspeed exists.

The stall speed will vary depending on the airplane's ______, altitude, and configuration (flap setting, etc.).

Thrust is the force which moves an aircraft through the ______.

Thrust is a reaction force described quantitatively by ______'s second and third laws.

Thrust is used to overcome the ______ of an airplane.

When a system expels or accelerates ______ in one direction, the accelerated mass will cause a force of equal magnitude in opposite direction.

The magnitude of the thrust depends on the amount of gas accelerated and on the difference in velocity of the gas through the ______.

A propeller converts shaft power from the engine into ______.

The propeller blade is an ______ and the definitions for chord, camber, thickness/chord ratio and aspect ratio are the same as those given previously for the wing.

The propeller accelerates a large mass of ______ rearwards thereby propelling the Aircraft forward.

Acceleration of ______ produces thrust propelling aircraft forward.