1609

Item 1609

OTHER: Rotor Concept - Reverse Velocity Utilization - Traversing Root Pitch Axis Pt. 3

Drawing:

Notes:

The forward velocity airfoil is in NVFoil as VR5.DAT

The reverse velocity airfoil is in NVFoil as VR%_RE_1.DAT

Data from NVFoil:

The angle of attack is 7º.
The number of poins is 100

	VR5.DAT	VR5_RE_1.DAT ⁽¹⁾
Cl:	1.134	1.938
Cd:	0.002	0.137
Cm:	-0.051	-0.216
Center of Pressure:	29% Chord	64% C \| -36% C⁽²⁾

(1) This is probably experiencing leading edge stall.

(2) 0.36 C from sharp edge.

More Notes:

If the sharp trailing edge could be given any radius when it is the leading edge than this should give a greater range of AoA before experiencing the leading edge stall.

Increase the blade thickness.

There appears to be an insignificant difference between the VR5 and the VR7; in profile, and center of pressure at various angles.

Concerns:

The possible need to relocate the root end's leading edge weight chordwise at 1P when in cruise.

Will the chordwise movement of the root end still allow for an aerodynamically clean faring to the hub?

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Initially displayed: January 24, 2008 ~ Last Revision: January 26, 2008

The above application of reverse velocity utilization in the main rotor(s) of a helicopter is openly and publicly disclosed on the Internet to negate an entity from patenting it, to the exclusion of all others whom may wish to use it. ~ Reference patent law 35 U.S.C. 102 A person shall be entitled to a patent unless - (a) the invention was known ... by others in this country, ..., before the invention thereof by the applicant for patent.