WIND TUNNEL INVESTIGATION OF A CIRCULATION CONTROLLED AIRFOIL ROTOR CONCEPT.
Abstract
A 6 foot diameter rigid rotor, employing circulation controlled blades, was tested in an 8 x 12 foot low speed wind tunnel. Circulation control was generated by injecting gas tangentially from slots in the two circular cylinder blades. The tip jet driven model was tested as a propeller and in the normal helicopter mode. Tip speeds up to 440 fps were attained for the model operating in the propeller mode, while advance ratios up to 0.8 were attained in the helicopter mode. A computer simulation of the rotor model was used to analyze the wind tunnel results. Comparison between selected wind tunnel results and the computer simulation are presented. Agreement between selected propeller mode results and the computer simulation was obtained by using peak inflow velocities measured by a high resolution pitotstatic probe. The correlation between the helicopter mode tests and the computer simulation is commensurate with the large model to tunnel ratio and the present model support system. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1968
- Accession Number
- AD0680464
Entities
People
- M. T. Harvey
- S. P. Tyler
- W. H. Gallaher
Organizations
- General Dynamics