Aircraft leading edge device systems and corresponding sizing methods
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United States of America Patent
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Apr 15, 2008
Grant Date -
Oct 13, 2005
app pub date -
Feb 27, 2004
filing date -
Feb 27, 2004
priority date (Note) -
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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.
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