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OTHER: Aerodynamics - Blade Profile - NACA 0006

For information related to the specific blade for the Unicopter see: UniCopter ~ Rotor - Blade - NACA 00xx

Drawing:

Characteristics:

Thickness	t/c	= 0.06
Leading Edge Circle	r/c	= 0.04
Center at	x/c	=
Center at	y/c	=

Airfoil with Different Angles of Attack:

Airfoil integral coefficients: Cl (lift), Cd (drag) and Cm (aerodynamic moment in respect to 1/4 of the chord). It's important to note that Cd is theoretically null in a 2-D non-viscous subsonic flow; hence this number is a measure of the numeric errors in the code and in the choice of the points.

The Cm is considered positive when pulling up.

The following calculations are from the freeware program NVFoil.

ά		[alpha] The angle of attack is the angle between the airfoil chord and the velocity vector.
c_l		Coefficient of lift; two-dimensional
c_d		Coefficient of drag; two-dimensional
c_m0		Coefficient of moment; two-dimensional. (pitching-moment coefficient) @ 25% of chord
x_cp		Location on X-axis of center of pressure as a percentage of chord from leading edge.
Airfoil & Tab	ά		c_l	c_d	c_l^3/2/c_d	c_m0	x_cp
NACA 0006	0		0.000	0.000		0.000	25
	1		0.116	-0.000		-0.0016	25
	2		0.233	0.000		-0.002	25
	4		0.465	0.001		-0.004	25
	6		0.696	0.001		-0.007	25
	8		0.927	0.002		-0.009	25

The maximum coefficient of lift (c_lMax) is approximately 0.85 at 9º angle of attack. [Source ~ TWS p.452]

General comments related to the NACA 0006 airfoil:

I think that this blade was used on the compound Bell UH-1, which reached a speed of 275 kts in level flight.

Last Revised: Sunday, February 11, 2009