AERODYNAMIC LOADS ON AN ISOLATED SHROUDED-PROPELLER CONFIGURATION FOR ANGLES OF ATTACK FROM -10 DEGREES TO 110 DEGREES
Abstract
An investigation of the division of loads between the propeller and the shroud of a shroudedpropeller configuration was conducted in the 17-foot test section of the Langley 300-MPH 7- by 10-foot tunnel. This investigation covered an angle-of-attack range from -10 to 110 degrees and a range of advance ratios (0 to 0.595) typical of the transition speed range of a tilt-duct VTOL aircraft. For the configurations with fixed blade angle (24 degrees at the three-quarter radius), the normal force and pitching moment developed by the propeller and spinner were only a relatively small part of the over-all normal force and pitching moment of either a stalled or an unstalled shroud. The ratio of the thrust of the propeller and spinner to total thrust was found to vary from about 0.4 in hovering to about 0.7 at the highest advance ratio of the tests, 0.595, with the shroud at zero angle of attack. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1962
- Accession Number
- AD0268842
Entities
People
- Kalman J. Grunwald
- Kenneth W. Goodson
Organizations
- National Aeronautics and Space Administration