In a wing and nacelle combination, where the nacelle is positioned below and forwardly of the wing leading edge, a wake control device to control a turbulent wake which is formed at the upper forward lip portion of the nacelle. This wake control device comprises a forward vortex generating portion t
In a wing and nacelle combination, where the nacelle is positioned below and forwardly of the wing leading edge, a wake control device to control a turbulent wake which is formed at the upper forward lip portion of the nacelle. This wake control device comprises a forward vortex generating portion to create a vortex which travels over the leading edge of the wing, and also a fence located at the middle third of the nacelle to control boundary layer air and thus properly locate the wake control vortex.
대표청구항▼
1. In a nacelle and wing combination, where said wing is swept and has a leading edge, a trailing edge, an upper surface and a lower surface, said nacelle being mounted below and forwardly of the leading edge of the wing, said nacelle having an outside surface and having a forward portion extending
1. In a nacelle and wing combination, where said wing is swept and has a leading edge, a trailing edge, an upper surface and a lower surface, said nacelle being mounted below and forwardly of the leading edge of the wing, said nacelle having an outside surface and having a forward portion extending forwardly of said wing leading edge and a forward inlet lip with an upper lip portion, the forward portion of the nacelle comprising a front third portion, a middle third portion, and a rear third portion, said wing having a first forward swept portion extending laterally and forwardly from said nacelle and a second rear swept portion extending laterally and rearwardly from said nacelle, said nacelle having first and second side portions adjacent said first and second wing portions, respectively, said wing and nacelle combination being characterized in that in a wing and nacelle alone configuration, with the wing in a high lift configuration and in a high lift/high angle of attack mode of operation, flow separates from said upper lip portion to form a highly turbulent wake which passes over the wing leading edge with said wake having first and second side edge portions at said first and second wing portions, respectively, said wake first side edge portion expanding laterally and rearwardly across said first forwardly swept wing portion so as to reduce lift, an improvement which is a wake control means located on said nacelle surface adjacent the first edge portion of the wake, said wake control means comprising a forward vortex generating portion extending outwardly from said nacelle surface and positioned rearwardly of said inlet lip of the nacelle, and a second fence portion positioned rearwardly of said vortex generating portion and extending lengthwise in said middle third portion of the nacelle, said forward vortex generating portion functioning primarily to initially generate a vortex which travels rearwardly and over said wing leading edge, and said fence portion controlling boundary layer air which flows upwardly and rearwardly along said nacelle first side surface portion so as to direct some of said boundary layer air away from said wing leading edge portion which is proximate to an upper part of said nacelle first side surface portion, and to energize other portions of said boundary layer air whereby said vortex becomes properly positioned adjacent the first side edge portion of the wake to limit expansion of the first side edge portion of the wake over the wing. 2. The improvement as recited in claim 1, wherein said wake control means has an elongate configuration having a lengthwise axis generally aligned with a lengthwise axis of said nacelle and aerodynamically contoured to limit drag for cruise mode of operation. 3. The improvement as recited in claim 2, wherein said vortex generating portion and said fence portion are aligned with one another and provide a substantially aerodynamically continuous wake control means. 4. The improvement as recited in claim 3, wherein said vortex generating portion has a height dimension from a center axis of said nacelle greater than a height dimension of the fence portion. 5. The improvement as recited in claim 2, wherein said vortex generating portion has a height dimension from a center axis of said nacelle greater than a height dimension of the fence portion. 6. The improvement as recited in claim 2, wherein said wake control means comprises a plurality of separate wake control members positioned at spaced lengthwise locations along said nacelle surface. 7. The improvement as recited in claim 2, wherein said vortex forming portion is located in said front third portion of the nacelle. 8. The improvement as recited in claim 7, wherein said nacelle has a cowl door located at said middle third portion, and said fence portion is mounted to said door, said vortex forming portion having a height greater than said fence portion. 9. In a nacelle and wing combination, where said wing is swept and has a leading edge, a trailing edge, an upper surface and a lower surface, said nacelle being mounted below and forwardly of the leading edge of the wing, said nacelle having an outside surface and having a forward portion extending forwardly of said wing leading edge and a forward inlet lip with an upper lip portion, the forward portion of the nacelle comprising a front third portion, a middle third portion, and a rear third portion, said wing having a first forward swept portion extending laterally and forwardly from said nacelle and a second rear swept portion extending laterally and rearwardly from said nacelle, said nacelle having first and second side portions adjacent said first and second wing portions, respectively, said wing and nacelle combination being characterized in that in a wing and nacelle alone configuration, with the wing in said high lift configuration and in a high lift/high angle of attack mode of operation, flow separates from said upper lip portion to form a highly turbulent wake which passes over the wing leading edge with said wake having first and second side edge portions at said first and second wing portions, respectively, said wake first side edge portion expanding laterally and rearwardly across said first forwardly swept wing portion so as to reduce lift, a method of controlling said wake by forming a vortex on said nacelle surface adjacent the first edge portion of the wake at a forward location rearward of said lip to cause said vortex to travel rearwardly over said wing leading edge, and providing a fence rearwardly of the vortex generating location with said fence extending lengthwise in said middle third portion of the nacelle, said fence controlling boundary layer air which flows upwardly and rearwardly along said nacelle first side surface portion so as to direct some of said boundary layer air away from said wing leading edge portion which is proximate to an upper part of said nacelle first side surface portion, and to energize other portions of said boundary layer air, whereby said vortex becomes properly positioned adjacent the first side edge portion of the wake to limit expansion of the first side edge portion of the wake over the wing. 10. The method as recited in claim 9, wherein said vortex is generated by wake control means having an elongate configuration having a lengthwise axis generally aligned with a lengthwise axis of said nacelle and aerodynamically contoured to limit drag for cruise mode of operation. 11. The method as recited in claim 9, wherein said vortex is generated by vortex generating portion which is aligned with said fence to provide a substantially aerodynamically continuous wake control means. 12. The method as recited in claim 11, wherein said vortex generating portion has a height dimension from a center axis of said nacelle greater than a height dimension of the fence portion. 13. A method of designing and building a nacelle and wing combination, where said wing is swept and has a leading edge, a trailing edge, an upper surface and a lower surface, said nacelle being mounted below and forwardly of the leading edge of the wing, said nacelle having an outside surface and having a forward portion extending forwardly of said wing leading edge and a forward inlet lip with an upper lip portion, the forward portion of the nacelle comprising a front third portion, a middle third portion, and a rear third portion, said wing having a first forward swept portion extending laterally and forwardly from said nacelle and a second rear swept portion extending laterally and rearwardly from said nacelle, said nacelle having first and second side portions adjacent said first and second wing portions, respectively, (a) determining whether a turbulent wake condition exists, when, with said wing and nacelle combination in a wing and nacelle alone configuration, with the wing in a high lift configuration and in a high lift/high angle of attack mode of operation, flow separates from said upper lip portion to form said highly turbulent wake which passes over the wing leading edge with said wake having first and second side edge portions at said first and second wing portions, respectively, and said wake first side edge portion expands laterally and rearwardly across said forwardly swept wing portion so as to reduce lift, (b) determining location of said first side edge portion of the wake as the wake leaves the upper lip portion at a forward part of said nacelle, (c) mounting a vortex generating means to the nacelle rearwardly of said lip and adjacent to said first side edge portion at a location to generate a vortex which travels rearwardly over the leading edge of the wing, (d) mounting a fence rearwardly of the vortex generating portion in the middle third portion of the nacelle side surface rearwardly of said vortex generating portion at a location to control boundary layer flow rearwardly and upwardly along the first side portion of the nacelle so as to position said vortex properly adjacent the first side edge portion of the wake and limit expansion of the first side edge portion of the wake over the wing. 14. The method as recited in claim 13, further comprising placing said vortex generating means and said fence in alignment with one another in a manner to provide a substantially aerodynamically continuous wake control means. 15. The method as recited in claim 14, wherein said vortex generating means is formed with a height dimension from a center axis of said nacelle greater than a height dimension of the fence. 16. The method as recited in claim 13, wherein said vortex generating means is formed with a height dimension from a center axis of said nacelle greater than a height dimension of the fence. 17. The method as recited in claim 13, further comprising forming said vortex generating means and said fence as a plurality of separate wake control members positioned at spaced lengthwise locations along said nacelle surface. 18. The method as recited in claim 13, wherein said vortex forming portion is located in said front third portion of the nacelle. 19. The method as recited in claim 18, wherein said nacelle has a cowl door located at said middle third portion, and said fence is mounted to said door, said vortex generating means having a height greater than said fence.
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이 특허에 인용된 특허 (1)
Pierce, Donald, Aircraft having improved strake configuration.
Perin Robert (Pibrac FRX) Jourdan Pierre (Blagnac FRX) Pauly Bernard (Blagnac FRX), Arrowlike aircraft wing equipped with a high-lift system and with a pylon for suspending the engine.
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