Study to determine division of aerodynamic loads between shroud and propeller; propeller contribution to overall normal force and pitching moment of VTOL configuration was found to be relatively small for stalled or unstalled shroud; ratio of thrust of propeller and spinner to total thrust was found to vary from 0.4 in hovering to 0.7 at highest advance ratio of tests, 0.595, with shroud at zero angle of attack.
Aerodynamic loads on isolated shrouded-propeller configuration for angles of attack from -10°
NASA -- Tech Notes
1962
29 pages
Report
English
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Aerodynamic characteristics of small-scale shrouded propeller at angles of attack from 0° to 90°
Engineering Index Backfile | 1955
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