Helicopter rotor blade
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United States of America Patent
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-
May 26, 1987
Grant Date -
N/A
app pub date -
Jun 19, 1984
filing date -
Jul 4, 1983
priority date (Note) -
Expired
status (Latency Note)
Importance
Abstract
An outboard region of a helicopter rotor blade of aerofoil cross section has a thickness to chord ratio not greater than twelve percent and an inboard region has a thickness to chord ratio greater than twelve percent. Preferably, the thickness to chord ratio of the inboard region is greater than eighteen percent and may increase towards the root end to about twenty four percent. The inboard region may extend outwardly to a position not exceeding sixty percent of an operating radius of the rotor blade.
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