Patent US4296900A successfully refreshed from Google Patents.
US4296900A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Airfoil construction
Assignee: Lockheed Martin Corp
•
Filing: 1979-04-23
•
Granted: 1981-10-27
•
Expires: 1999-04-23
Abstract
Abstract A dual-configuration airfoil having a thin profile which is adapted to foster high-speed flight, and having a pivotable portion on the upper surface which is movable upwardly for selectively increasing the thickness of the airfoil. In one embodiment, the pivotable portion pivots about an axis which coincides generally with the leading edge of the airfoil. The thickness of the airfoil when the pivotable portion is fully raised is about twice the thickness of the airfoil when the pivotable portion is fully retracted. A rigid connecting section forms part of the airfoil's upper surface immediately behind the pivotable portion. The connecting section is also movable, such that a substantially continuous and rigid surface is presented to the air moving over the airfoil's upper surface during such times as the pivotable portion is being pivoted upward and downward--as well as when the pivotable portion is fixedly held. A rearwardly directed nozzle is located adjacent the aft edge of the pivotable portion, and it is oriented such that it can discharge a gaseous fluid (e.g., air) over the connecting section. A source of pressurized fluid, such as an engine-driven compressor or a fan, is adapted to be connected with said nozzle. And, a control or regulating valve is provided for adjusting the discharge of fluid from said source over the connecting section. Preferably, the connecting section is configured so as to cause the air which flows thereover to decelerate in a controlled manner, and preferably the deceleration occurs faster nearer the leading part of said section than near the trailing part thereof. In one embodiment, the means for adjusting the discharge of fluid from said nozzle includes a linkage which is connected to a movable control surface, such as a trailing edge flap. In this way, moving the flap down to a landing position can automatically cause fluid to be discharged from the nozzle and over a selected portion of the airfoil.
Inventors
- 👤 Kenneth M. Krall
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-30 22:51
CPC Classifications
B; B64; B64C; B64C3/00; B64C3/38; B64C3/44; B64C3/48; B64C2220/00; Y; Y02; Y02T; Y02T50/00; Y02T50/10
Claims Analysis
Total Claims: 7
Claim 1
Independent Claim
258 words
An airfoil construction, comprising: (a) upper and lower surface structure which connects leading and trailing edges so as to form a relatively thin profile which is adapted to foster high speed flight, with one portion of the upper surface structure being pivotable upward about a hinge line that coincides generally with the leading edge of the airfoil, for increasing the thickness of the airfoil, and the chordwise length of said pivotable portion being substantially less than the chord length; (b) a connecting section which forms part of the airfoil upper surface structure immediately aft of the pivotable portion, and said section being positionable for presenting a substantially continuous and rigid surface to the air moving over the upper surface structure during such times as the pivotable portion is being pivoted upward and downward, and the connecting section cooperating with the remainder of the airfoil upper surface when the connecting section is lowered to establish an elongated convex cross section for high speed fight, and the connecting section also cooperating with the remainder of the airfoil upper surface when the connecting section is fully raised to establish a compound curvature having both concave and convex portions for fostering low speed flight; (c) a rearwardly directed nozzle located adjacent the aft edge of the pivotable portion and oriented such that it can discharge a gaseous fluid over the connecting section; (d) a source of pressurized fluid adapted to be connected with said nozzle; and (e) control means for adjusting the discharge of fluid from said source over the connecting section.
Claim 2
Dependent Claim
258 words
An airfoil construction, comprising: (a) upper and lower surface structure which connects leading and trailing edges so as to form a relatively thin profile which is adapted to foster high speed flight, with one portion of the upper surface structure being pivotable upward about a hinge line that coincides generally with the leading edge of the airfoil, for increasing the thickness of the airfoil, and the chordwise length of said pivotable portion being substantially less than the chord length; (b) a connecting section which forms part of the airfoil upper surface structure immediately aft of the pivotable portion, and said section being positionable for presenting a substantially continuous and rigid surface to the air moving over the upper surface structure during such times as the pivotable portion is being pivoted upward and downward, and the connecting section cooperating with the remainder of the airfoil upper surface when the connecting section is lowered to establish an elongated convex cross section for high speed fight, and the connecting section also cooperating with the remainder of the airfoil upper surface when the connecting section is fully raised to establish a compound curvature having both concave and convex portions for fostering low speed flight; (c) a rearwardly directed nozzle located adjacent the aft edge of the pivotable portion and oriented such that it can discharge a gaseous fluid over the connecting section; (d) a source of pressurized fluid adapted to be connected with said nozzle; and (e) control means for adjusting the discharge of fluid from said source over the connecting section.
Claim 3
Dependent Claim
247 words
In combination: (a) an airfoil; (b) a nozzle adapted to direct a jet of gaseous fluid over an upper surface of the airfoil; (c) a source of pressurized gaseous fluid; (d) control means for selectively placing the source of pressurized fluid in communication with the nozzle; (e) a hinged upper plate at the frontal portion of said airfoil's upper surface; and (f) a movable connecting section of rigid material which extends between the hinged upper plate and the remainder of the airfoil's upper surface when the upper plate is pivoted upward about its hinge line, and the connecting section cooperating with the remainder of the airfoil upper surface when the connecting section is lowered to establish an elongated convex cross-section for high speed flight, and the connecting section also cooperating with the remainder of the airfoil upper surface when the connecting section is fully raised to establish a compound curvature having both concave and convex portions for fostering low speed flight, and the movable connecting section including a surface portion which is defined by the formula: y=(h/2) cos 0.13(x/δ), wherein y=the locus of points on the surface downstream from the nozzle, for respective distances x from said nozzle, x=the distance downstream from the nozzle, measured in a direction parallel to the main-stream airflow at the nozzle, δ=the boundary layer thickness of the airflow immediately above the nozzle, and h=the height of the nozzle above that point where deceleration of the airflow essentially ends, i.e., the "step height".
Claim 4
Dependent Claim
247 words
In combination: (a) an airfoil; (b) a nozzle adapted to direct a jet of gaseous fluid over an upper surface of the airfoil; (c) a source of pressurized gaseous fluid; (d) control means for selectively placing the source of pressurized fluid in communication with the nozzle; (e) a hinged upper plate at the frontal portion of said airfoil's upper surface; and (f) a movable connecting section of rigid material which extends between the hinged upper plate and the remainder of the airfoil's upper surface when the upper plate is pivoted upward about its hinge line, and the connecting section cooperating with the remainder of the airfoil upper surface when the connecting section is lowered to establish an elongated convex cross-section for high speed flight, and the connecting section also cooperating with the remainder of the airfoil upper surface when the connecting section is fully raised to establish a compound curvature having both concave and convex portions for fostering low speed flight, and the movable connecting section including a surface portion which is defined by the formula: y=(h/2) cos 0.13(x/δ), wherein y=the locus of points on the surface downstream from the nozzle, for respective distances x from said nozzle, x=the distance downstream from the nozzle, measured in a direction parallel to the main-stream airflow at the nozzle, δ=the boundary layer thickness of the airflow immediately above the nozzle, and h=the height of the nozzle above that point where deceleration of the airflow essentially ends, i.e., the "step height".
Claim 5
Dependent Claim
39 words
The combination as claimed in claim 2 wherein the ratio of the thickness of the airfoil when the hinged upper plate is fully raised in comparison to its thickness when the hinged plate is fully collapsed is about 2.
Claim 6
Independent Claim
256 words
The method of achieving boundary layer control in a system which utilizes vented gas from an aircraft engine compressor, with there being a valve between the compressor and a nozzle on an airfoil, comprising the steps of: (a) partially opening the valve during aircraft take-off, when the engine is operating at full thrust and a substantial pressure is realizable from the compressor; (b) fully opening the valve during aircraft landing, when the engine is operating at greatly reduced thrust and a correspondingly lower pressure is realizable from the compressor; and (c) venting compressed air from said compressor through a nozzle on the upper surface of at least one airfoil, and the airfoil being convertible from a thin cruise mode wherein the airfoil's upper surface is convex to a thicker mode for takeoff and landing, and the airfoil's thicker configuration including a compound curvature on the airfoil's upper surface having a generally convex shape which is followed by a generally concave cross-section, and the nozzle being located immediately ahead of the transition region where the airfoil thickness begins to change from an increasing thickness to a decreasing thickness as measured in a chordwise direction, such that compressed air is vented from the nozzle at a location just ahead of a generally convex portion of the thickened airfoil, and the mixture of mainstream airflow and vented compressor air immediately thereafter passes through a deceleration region having a generally concave shape, whereby substantial deceleration of the mainstream airflow occurs over the airfoil and ahead of any trailing edge flap.
Claim 7
Independent Claim
256 words
The method of achieving boundary layer control in a system which utilizes vented gas from an aircraft engine compressor, with there being a valve between the compressor and a nozzle on an airfoil, comprising the steps of: (a) partially opening the valve during aircraft take-off, when the engine is operating at full thrust and a substantial pressure is realizable from the compressor; (b) fully opening the valve during aircraft landing, when the engine is operating at greatly reduced thrust and a correspondingly lower pressure is realizable from the compressor; and (c) venting compressed air from said compressor through a nozzle on the upper surface of at least one airfoil, and the airfoil being convertible from a thin cruise mode wherein the airfoil's upper surface is convex to a thicker mode for takeoff and landing, and the airfoil's thicker configuration including a compound curvature on the airfoil's upper surface having a generally convex shape which is followed by a generally concave cross-section, and the nozzle being located immediately ahead of the transition region where the airfoil thickness begins to change from an increasing thickness to a decreasing thickness as measured in a chordwise direction, such that compressed air is vented from the nozzle at a location just ahead of a generally convex portion of the thickened airfoil, and the mixture of mainstream airflow and vented compressor air immediately thereafter passes through a deceleration region having a generally concave shape, whereby substantial deceleration of the mainstream airflow occurs over the airfoil and ahead of any trailing edge flap.
References Cited (Backward Citations)
US1803915A
Cited
US1760726A
Cited
US1918897A
Cited
US2964264A
Cited
US2886264A
Cited
US3132826A
Cited
US3265331A
Cited
US3724784A
Cited
US3887147A
Cited
US3807663A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1984-10-26 | 1985-04-27 | 1985-10-27 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1988-10-26 | 1989-04-27 | 1989-10-27 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1992-10-26 | 1993-04-27 | 1993-10-27 | $7700.00 | Window Closed / Lapsed |