Aircraft leading edge device systems and corresponding sizing methods
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Accused Products
Abstract
Aircraft leading edge device systems and methods for sizing such systems are disclosed. In one embodiment, a spanwise lift coefficient distribution for an airfoil corresponding to at least one design condition and at least one aircraft angle of attack is identified, and a leading edge device chord length is sized to at least approximately achieve the selected spanwise lift coefficient distribution. In another embodiment, a spanwise distribution of aircraft angles of attack corresponding to local maximum lift coefficients for an airfoil operated at a design condition is identified, and a leading edge device chord length at each of a plurality of spanwise locations is sized to achieve the distribution of aircraft angles of attack corresponding to local maximum lift coefficients. In yet another embodiment, a leading edge device chord length is tapered in two, at least approximately opposite, spanwise directions.
111 Citations
50 Claims
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1-28. -28. (canceled)
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29. An aircraft system comprising:
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an airfoil having a spanwise portion, the spanwise portion having a plurality of spanwise locations; and
a leading edge device arrangement coupled to the spanwise portion, the leading edge device arrangement including at least a portion of at least one leading edge device, wherein a leading edge device chord length at each of the plurality of spanwise locations is at least approximately equal to the smallest leading edge device chord length required to provide a local maximum lift coefficient when the airfoil is operated at at least one selected design condition and a selected aircraft angle of attack. - View Dependent Claims (30, 31, 32, 33, 34)
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35. An aircraft system comprising:
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an airfoil having a spanwise portion, the spanwise portion having a plurality of spanwise locations; and
leading edge high lift means for increasing airfoil performance at high aircraft angles of attack positioned proximate to the spanwise portion wherein a high lift means chord length at each of the plurality of spanwise locations is at least approximately proportional to an approximately smallest high lift means chord length required to provide a local maximum lift coefficient when the airfoil is operated at at least one selected design condition and a selected aircraft angle of attack. - View Dependent Claims (36, 37, 38)
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39. (canceled)
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41. An aircraft system, comprising:
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an airfoil having a spanwise portion, the spanwise portion having a plurality of spanwise locations; and
a leading edge device arrangement coupled to the spanwise portion, the leading edge device arrangement including at least a portion of at least one leading edge device, wherein a leading edge device chord length at each of the plurality of spanwise locations is at least approximately proportional to a leading edge device chord length at each location determined to provide a selected lift coefficient distribution when the airfoil is operated at at least one selected design condition and at least one selected aircraft angle of attack, wherein the leading edge device arrangement has at least two tapered portions, including;
a first tapered portion wherein the leading edge device chord length is tapered in a first spanwise direction; and
a second tapered portion wherein the leading edge device chord length is tapered in a second spanwise direction approximately opposite the first direction, the leading edge device chord length varying in a manner at least approximately the same as the manner in which the leading edge device chord length at each location determined to provide the selected lift coefficient distribution varies across the spanwise portion. - View Dependent Claims (40, 42, 43, 44)
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45. (canceled)
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47. An aircraft system, comprising:
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an airfoil having a spanwise portion, the spanwise portion having a plurality of spanwise locations; and
a leading edge device arrangement coupled to the spanwise portion, the leading edge device arrangement including at least a portion of at least one leading edge device, wherein a leading edge device chord length at each of the plurality of spanwise locations is at least approximately proportional to a leading edge device chord length at each location determined to provide a selected spanwise distribution of aircraft angles of attack corresponding to local maximum lift coefficients when the airfoil is operated at at least one selected design condition, wherein the leading edge device arrangement has at least two tapered portions, including;
a first tapered portion wherein the leading edge device chord length is tapered in a first spanwise direction; and
a second tapered portion wherein the leading edge device chord length is tapered in a second spanwise direction approximately opposite the first spanwise direction, the first and second portions having a combined distribution of chord lengths at least approximately the same as the determined leading edge device chord lengths. - View Dependent Claims (46, 48, 49, 50)
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Specification