Flow in which the density of the fluid elements can change from point to point.

It is a type of flow that has no mass diffusion, no viscosity (friction), and no thermal conduction.

A hinged portion of the trailing or leading edge that can be deflected downwards and thus create a camber increase.

The flap forms part of the lower surface of the trailing edge of the wing, with the upper surface contour not affected when the flap is lowered.

A type of flap that travels backwards and downwards, giving initially an increase in wing area, and then an increase in camber.

The camber of a leading-edge flap can be increased to improve efficiency by offering a better leading-edge profile.

It is a small auxiliary airfoil fixed to the wing 's leading edge.

An airfoil that is also known as cambered airfoils. It has a different upper and lower surfaces such that the chord line is placed above with large curvature.

It is an airfoil with mirrored upper and lower surfaces such that the chord line and mean camber line are the same producing no lift at zero angle of attack.

The principle which states that an increase in the speed of a fluid occurs simultaneously with a decrease in pressure or a decrease in the fluid's potential energy is named after the Swiss mathematician _____?

Formed on March 3, 1915, with a charter to "supervise and direct the scientific study of the problems of flight, with a view to their practical solution."

It is a type of boundary layer control that is accomplished by jetting high-velocity air from vents through the upper surface of the wing just below the leading edge.

The line joining the midpoints between the upper and lower surfaces of an airfoil and measured normal to the chord line.

The velocity increases in the convergent portion of the duct, reaching a maximum value of velocity at the minimum area of the duct. This minimum area is called the ________.

It is primarily used on low-speed aircraft and where very fast take-off and landing are not necessary.

It gives CLMAX a greater increase than the plain or split flap, and much less drag, but has a more complicated design.

Used on the inboard section to facilitate root stall on a swept wing, because they are less effective than the opposite variable camber.

Its typical features are flattened upper surface, a highly cambered or curved aft section and greater leading edge radius.

The height of profile measured normal to the chord line.