Fluid reaction surfaces (i.e. – impellers) – Specific blade structure – Radial flow devices
Patent
1979-12-05
1982-04-20
Powell, Jr., Everette A.
Fluid reaction surfaces (i.e., impellers)
Specific blade structure
Radial flow devices
416DIG2, B64C 2746, B64C 314
Patent
active
043256759
ABSTRACT:
The present invention relates to a blade profile for rotary wing of an aircraft, comprising, between the leading edge and the trailing edge, a convex upper surface and a non-concave lower surface, wherein, at the point of maximum curvature of the leading edge, the radius of curvature Ro is approximately defined by the expression Ro=1.7 C. e.sub.max.sup.2, in which C represents the chord and e.sub.max the relative thickness of said profile and the portion of lower surface adjacent the leading edge extends to about 20% of the chord from said leading edge and presents a very small general curvature decreasing continuously in the direction of the trailing edge up to the point of minimum curvature of the lower surface. The invention is more particularly applicable to obtaining rotary wings, for example for helicopters, capable of very high performances both when hovering, and in high speed flight, as well as during manoeuvres.
REFERENCES:
patent: 1981392 (1934-11-01), Selman
patent: 2257260 (1941-09-01), Kartveli
patent: 2281272 (1942-04-01), Davis
patent: 2441151 (1948-05-01), Jones
patent: 2448698 (1948-09-01), Biot et al.
patent: 2450440 (1948-10-01), Mills
patent: 3173490 (1965-03-01), Stuart
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patent: 4240598 (1980-12-01), Espin et al.
de Paul Michel V.
Gallot Jacques
Thibert Jean-Jacques
Vingut Georges
Office National d'Etudes etc.
Powell Jr. Everette A.
Societe Nationale Industrielle Aerospatiale
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