The Effect of Shaft Angle on Performance of a Circulation Control High-Speed Rotor at an Advance Ratio of 0.7.
Research and development rept.,
DAVID W TAYLOR NAVAL SHIP RESEARCH AND DEVELOPMENT CENTER BETHESDA MD AVIATION AND SURFACE EFFECTS DEPT
Pagination or Media Count:
As part of the on-going Circulation Control Rotor Technology Program at the David W. Taylor Naval Ship Research and Development Center, a high-speed rotor model designated the Reverse Blowing Circulation Control Rotor RBCCR was evaluated in a wind tunnel in the forward flight mode. The RBCCR models was used to evaluate the effects of rotor shaft angle of attack on rotor performance at the transitional advance ratio of mu 0.7. The test variables included rotor thrust, blade collective pitch angle, tip Mach number, and rotor shaft angle. The RBCCR model has demonstrated both the lift and trim capabilities required in the transitional flight regime. The model has also shown that rotor efficiency and power sharing between shaft power and compressor power can be controlled by rotor shaft angle at an advance ratio of 0.7.
- Fluid Mechanics