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US 4,702,441 AGranted
Aircraft wing stall control device and method
AssigneeThe Boeing Company
InventorTimothy Wang
Life of this patent
Estimating the term…
Abstract
A swept wing having a leading edge flap which in its deployed position forms a slot with the forward end portion of the wing. An elongate strip is positioned on the forward portion of the wing in a manner that when the flap is deployed to form the slot, this strip protrudes into the airstream that passes upwardly through the slot. This creates a stall condition in the area of the strip to produce the desired pitch characteristics for safe recovery from stall. In the cruise configuration, where the flap is positioned against the leading edge of the wing, this strip is aerodynamically concealed.
Claims20
In a wing of an aircraft, where the wing comprises:
- (a) a main wing structure having an upper aerodynamic surface, a lower aerodynamic surface, and a forward surface portion that extends upwardly toward said upper aerodynamic surface;
- (b) a leading edge member which is moveable between a stowed position for cruise mode where the device aerodynamically conceals the surface of the main wing structure, and a deployed position for high-lift mode where the device forms with the forward surface portion of the main wing structure a slot for passage of air upwardly therethrough and over the wing upper surface;
- (c) said wing being characterized in that within a predetermined range of high angles of attack and with the leading edge member deployed, there is an aerodynamic condition of initial stall at a first spanwise location of the wing, without a corresponding pattern of stall developing at a second spanwise location of the wing, with said aerodynamic condition producing an undesired pitching moment;
- the improvement comprising a flow disturbing means positioned at said slot at said second spanwise location in a manner that with the leading edge member in said stowed position, the flow disturbing means is aerodynamically concealed by the leading edge member, and with the leading edge member in its deployed position, said flow disturbing means is exposed aerodynamically to antiflow in said slot to disturb the airflow that proceeds upwardly through said slot and over said wing, so as to create a disturbance which creates a desired stall condition at said second location.
1 more element
In a wing of an aircraft, where the wing comprises:
- (a) a main wing structure having an upper aerodynamic surface, a lower aerodynamic surface, and a forward surface portion that extends upwardly toward said upper aerodynamic surface;
- (b) a leading edge member which is moveable between a stowed position for cruise mode where the device aerodynamically conceals the surface of the main wing structure, and a deployed position for high-lift mode where the device forms with the forward surface portion of the main wing structure a slot for passage of air upwardly therethrough and over the wing upper surface;
- (c) said wing being characterized in that within a predetermined range of high angles of attack and with the leading edge member deployed, there is an aerodynamic condition of initial stall at or first spanwise location of the wing, without a corresponding pattern of stall developing at a second spanwise location of the wing, with said aerodynamic condition producing an undesired pitching moment;
- a method of alleviating said undesired pitching moment, said method comprising:
- a. providing a flow disturbing merans positioned at said slot and said second spanwise location;
- b. positioning the leading edge member in said stowed position so that the flow disturbing means is aerodynamically concealed by the leading edge member;
- c. positioning the leading edge member in its deployed position so that said flow distrubing means is exposed aerodynamically to airflow in said slot to disturb the airflow that proceeds upwardly through said slot and over said wing, so as to create a disturbance which creates a desired stall condition at said second location.
4 more elements
Dependencies are inferred from the claim text.