Helicopter rotor blades
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United States of America Patent
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Apr 6, 1993
Grant Date -
N/A
app pub date -
Oct 23, 1991
filing date -
Oct 24, 1990
priority date (Note) -
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Abstract
A helicoper rotor blade includes at its outer end a tip vane having a mean chord length greater than fifty percent of a chord length of a blade central portion and a span length greater than fifty percent of the blade chord which in operation generates two approximately equal strength tip vortices to reduce an acoustic impulse and a resulting noise known as blade slap.
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