Claims
- 1. An airfoil arrangement comprising:an airfoil; an engine including an engine nacelle; a pylon connecting said engine to said airfoil; a high lift leading edge flap movably connected to said airfoil so as to be extendable into an extended flap position and retractable into a retracted flap position relative to said airfoil, wherein an open space and a corresponding aerodynamic gap is formed between a leading edge portion of said airfoil, said pylon and a side edge of said leading edge flap facing said pylon, when said leading edge flap is in said extended flap position; and an auxiliary high lift device that is movably arranged so as to be extendable into an extended device position and retractable into a retracted device position, wherein said auxiliary high lift device in said extended device position is positioned in said open space to cooperate with said leading edge flap in said extended flap position and to at least partly close said aerodynamic gap, and wherein said auxiliary high lift device in said retracted device position is integrated into an outer contour of at least one of said nacelle and said pylon.
- 2. The airfoil arrangement according to claim 1, wherein said leading edge flap is an inboard leading edge flap arranged between said pylon and a root end of said airfoil adapted to be connected to an aircraft fuselage, and said side edge of said leading edge flap is an outwardly facing side edge of said leading edge flap that faces away from said root end of said airfoil.
- 3. The airfoil arrangement according to claim 1, wherein said auxiliary high lift device comprises an aerodynamically contoured auxiliary flap that aerodynamically closes said open space when said auxiliary flap is in said extended device position.
- 4. The airfoil arrangement according to claim 1, wherein said high lift leading edge flap is a leading edge slat.
- 5. The airfoil arrangement according to claim 1, wherein said high lift leading edge flap is a Krueger device.
- 6. The airfoil arrangement according to claim 1, wherein said high lift leading edge flap is a bent nose or drooped nose device.
- 7. The airfoil arrangement according to claim 1, wherein said auxiliary high lift device is configured and arranged in said extended device position so as to respectively increase a maximum lift and a critical angle of attack of a portion of said airfoil located flow downstream from said auxiliary high lift device.
- 8. The airfoil arrangement according to claim 1, wherein said pylon is a short pylon connecting said engine to said airfoil in a close-mounted engine configuration.
- 9. The airfoil arrangement according to claim 1, wherein said auxiliary high lift device is movably mechanically connected directly to said pylon, said pylon has a recess therein, and said auxiliary high lift device is received flushly in said recess in said retracted device position.
- 10. The airfoil arrangement according to claim 1, wherein said auxiliary high lift device is movably mechanically connected directly to said engine nacelle, said engine nacelle has a recess therein, and said auxiliary high lift device is received flushly in said recess in said retracted device position.
- 11. The airfoil arrangement according to claim 1, wherein said auxiliary high lift device comprises an auxiliary slat having a trapezoidal top view plan shape.
- 12. The airfoil arrangement according to claim 1, wherein said auxiliary high lift device comprises an auxiliary flap having a trapezoidal top view plan shape.
- 13. The airfoil arrangement according to claim 1, wherein said auxiliary high lift device comprises a nacelle flap door that is pivotably connected to said nacelle, that can be selectively pivoted down flushly into said outer contour of said nacelle in said retracted device position, and that can be selectively pivoted up from said nacelle to at least partially aerodynamically close said aerodynamic gap in said extended device position.
- 14. The airfoil arrangement according to claim 1, wherein said auxiliary high lift device in said extended device position forms, in said aerodynamic gap, an aerodynamically effective extension of said leading edge flap in said extended flap position.
Priority Claims (1)
Number |
Date |
Country |
Kind |
199 10 551 |
Mar 1999 |
DE |
|
PRIORITY CLAIM
This application is based on and claims the priority under 35 U.S.C. §119 of 199 10 551.0, filed on Mar. 10, 1999, the entire disclosure of which is incorporated herein by reference.
US Referenced Citations (17)
Foreign Referenced Citations (3)
Number |
Date |
Country |
19743907 |
Dec 1998 |
DE |
2555960 |
Jun 1985 |
FR |
53-98699 |
Aug 1978 |
JP |
Non-Patent Literature Citations (1)
Entry |
“Leading Edge Devices”, pp. 113-120, Aerodynamics, Aeronautics, and Flight Mechanics, Barnes W. McCormick, John Wiley Publishers (1979). |