B519

Item B519

DESIGN: SynchroLite ~ Rotor - Hub - 3-blade - 'Absolutely' Rigid Rotor & Rieseler Control

Notes:

Patents:

US 1,777,678. W. Rieseler et al

US 1,975,124. W. Rieseler and Kreiser

Reports:

The Aerodynamic Analysis of the Gyroplane Rotating-Wing System. ~ Report No. 492.

Wind-Tunnel Tests of a 10-foot-diameter Gyroplane Rotor. ~ Report No. 536.

Airfoils:

The airfoil used in the NACA wind tunnel test [Report No.536] was the symmetrical NACA 0015.

The following values are from NVFoil 10.1

	Center of Pressure (as % of chord)
Angle of Attack:	NACA 0012	8-H-12	VR-7
-3	26	31
-1	26	58	53
0	26	4	42
+3	26	22	33
+6	26	23	30
+9	26	24	29
+12	26	25	28

Check the above and other airfoils. I am trying to find the series where the CP move aft as the AoA gets larger since this should/may act as a damper

Miscellaneous:

This picture and text might be of interest; particularly because the gyroplane has a rigid rotor. Flight Research at NASA Langley Research Center
Description of Gyroplane

"The next major advance in autogyros came on August 5, 1931. This was the first flight of the Wilford WRK. This new autogyro replaced the hinged rotors with a rigid rotor with cyclic pitch variation. Cyclic pitch variation is a method where the pitch of the blades is changed as they spin. The pitch is lowered when they are moving in the direction of the aircraft, and raised when they are moving in the opposite direction. This does the same thing as flapping to balance the lift created by the blades. The WRK was the first autogyro to successfully fly with a rigid rotor. "

Last Revised: December 10, 2007