Propeller blade for aircraft propulsion

Details Propeller blade for aircraft propulsion Propeller blade for aircraft propulsion

1985-04-19

1987-03-24

Garrett, Robert E.

Fluid reaction surfaces (i.e., impellers)

Specific blade structure

Radial flow devices

416DIG2, 244 35R, B64C 1118

Patent

active

046522131

ABSTRACT:
The external part at least of a propeller blade, having a maximum relative thickness between about 2 and 6%, has a profile whose thickness variation law along the chord comprises a first zone (I) going from the leading edge to about 8% of the length of the chord in which the curvature decreases rapidly, from a maximum value at the leading edge, followed by a second zone (II) extending between about 8% of the chord and midships in which the curvature decreases linearly. In a third zone, extending from midships to 75 to 85% of the chord, the curvature is substantially constant. A fourth zone (IV), extending from the end of the third zone (typically at 80% of the chord) to the trailing edge, comprises a curvature inversion.

REFERENCES:
patent: 3343512 (1967-09-01), Rasmussen
patent: 3946688 (1976-03-01), Gornstein et al.
patent: 4142837 (1979-03-01), De Simone
patent: 4240598 (1980-12-01), Vinas Espin et al.
patent: 4325675 (1982-04-01), Gallot et al.
patent: 4412664 (1983-11-01), Noonan
patent: 4416434 (1983-11-01), Thibert et al.
patent: 4459083 (1984-07-01), Bingham
Abbott et al., "Theory of Wing Sections", N.Y., Dover, 1959, pp. 508-509.

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