초록 ▼

A wing-mounted pod for preventing an unstable increase in the pitching moment of a swept-wing aircraft due to increasing speed and angle of attack is disclosed. This invention is for use on a swept-wing aircraft of the type having a nonlinear, unstable increase in its pitching moment due to a loss o

A wing-mounted pod for preventing an unstable increase in the pitching moment of a swept-wing aircraft due to increasing speed and angle of attack is disclosed. This invention is for use on a swept-wing aircraft of the type having a nonlinear, unstable increase in its pitching moment due to a loss of lift at the outboard wing above a predetermined angle of attack at high Mach numbers. For an aircraft having a single, strut-mounted engine on each wing, the pod is placed along the intersection of the upper surface of the wing and the inboard side of the engine mounting strut. The pod prevents an increase in the pitching moment by inducing the formation of a shock in the air flowing over the upper surface of the inboard wing at the same angle of attack at which the outboard wing loses lift. The shock causes localized flow separation on the inboard wing, thereby preventing the increase in pitching moment otherwise experienced by the aircraft.

대표청구항 ▼

In an aircraft of the type having a nonlinear, unstable increase in the pitching moment above a predetermined angle of attack for a predetermined aircraft speed, said aircraft having a wing with a leading edge and an upper surface, an improvement comprising: means located on said upper surface of sa

In an aircraft of the type having a nonlinear, unstable increase in the pitching moment above a predetermined angle of attack for a predetermined aircraft speed, said aircraft having a wing with a leading edge and an upper surface, an improvement comprising: means located on said upper surface of said wing for forming a shock in the air flowing over the upper surface of said wing at said predetermined aircraft angle of attack of said wing and at an aircraft speed above a Mach number of approximately 0.6, said shock causing localized separation of the air flowing over said wing beginning at the trailing edge of said wing to prevent said increase in said pitching moment.