[PDF] Aerodynamic Characteristics Of A 4 Foot Diameter Ducted Fan Mounted On The Tip Of A Semispan Wing eBook

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Aerodynamic Characteristics of a 4-foot-diameter Ducted Fan Mounted on the Tip of a Semispan Wing

Kenneth W. Mort
Aerodynamic Characteristics of a 4-foot-diameter Ducted Fan Mounted on the Tip of a Semispan Wing by Kenneth W. Mort PDF

Author : Kenneth W. Mort
Publisher :
Page : 38 pages
File Size : 26,52 MB
Release : 1962
Category : Airplanes
ISBN :

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Power, free-stream velocity, and duct angle of attack were varied at several wing angles of attack to define the aerodynamic characteristics of the ducted fan, wing, and of the ducted fan wing together. At large duct angles of attack, the inside of the upstream duct lip stalled causing a rapid change in the duct pitching moments and an accompanying increase in the power required. At low horizontal velocities, this lip stall would probably limit the rate of descent of a vehicle with a wing-tip-mounted ducted fan. During low-speed, level, unaccelerated flight (30 to 80 knots) it appeared that a vehicle, with a configuration similar to that examined, would require less power if it were supported by a wing and ducted fans than if it were supported only by ducted fans. (Author).

Aerodynamic Characteristics of a Powered Semispan Tilting-shrouded-propeller VTOL Model in Hovering and Transition Flight

Kenneth W. Goodson
Aerodynamic Characteristics of a Powered Semispan Tilting-shrouded-propeller VTOL Model in Hovering and Transition Flight by Kenneth W. Goodson PDF

Author : Kenneth W. Goodson
Publisher :
Page : 52 pages
File Size : 48,14 MB
Release : 1962
Category : Aerodynamics
ISBN :

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"An investigation of the aerodynamic characteristics of a powered semispan tilting-shrouded-propeller configuration has been conducted in the 17-foot test section of the Langley 300-MPH 7- by 10-foot tunnel. The wing had an aspect ratio of 2.67 (based on wing span of 60 inches), a taper ratio of 0.67, and an NACA 2418 airfoil section with a 15-inch-diameter shrouded propeller mounted on the tip. The test results show that large nose-up pitching moments are obtained at transitional speeds of about 40 knots and duct angle of about 70°. Decelerating flight procedures further increases in the nose-up moment. Ground proximity reduces the nose-up pitching moments. The large nose-up moments can be trimmed by use of duct-exit control vanes. The results show that unloading the duct (shroud) by flying at a wing angle of attack of 15° reduces the power required by about 30 percent at 50 knots. Duct-lip stall produces large increases in power required. The results in general show that full-scale aerodynamic simulation can be made with small-scale wind-tunnel models if duct-lip separation at low Reynolds numbers is avoided."--Summary.

Keywords Index to U.S. Government Technical Reports

United States. Department of Commerce. Office of Technical Services
Keywords Index to U.S. Government Technical Reports by United States. Department of Commerce. Office of Technical Services PDF

Author : United States. Department of Commerce. Office of Technical Services
Publisher :
Page : 990 pages
File Size : 36,2 MB
Release : 1962
Category : Government publications
ISBN :

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