A Wind-tunnel Investigation of a 4-foot-diameter Ducted Fan Mounted on the Tip of a Semispan Wing PDF Download
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Author: Paul F. Yaggy
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 36
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Book Description
Author: Paul F. Yaggy
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 36
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Book Description
Author: Kenneth W. Mort
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 38
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Book Description
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).
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 204
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Book Description
Author: Michael D. Falarski
Publisher:
ISBN:
Category : Short take-off and landing aircraft
Languages : en
Pages : 60
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Book Description
The longitudinal aerodynamic characteristics of a semispan wing dellected-slipstream configuration with a double-slotted flap and and auxiliary wing were determined. The model was powered by two low-pressure-ratio ducted fans. A comparison of static test results with results obtained from various propeller-driven configurations indicates that the turning effectiveness of fan-powered deflected-slipstream configurations can be correlated with propeller-powered configurations with the same flap-chord to slipstream-diameter ratio. The turning effectiveness of the auxiliary wing was essentially the same as would be produced by a conventional slotted flap system with the same flap-chord to slipstream-diameter ratio. The auxiliary wing reduced the thrust required at low speeds as would be expected due to the increase in lifting surface area.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 450
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Book Description
Author: Kalman J. Grunwald
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 64
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Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 448
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Book Description
Author: Kenneth W. Mort
Publisher:
ISBN:
Category : Ducted fans
Languages : en
Pages : 38
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Book Description
Author: Paul F. Yaggy
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 20
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Book Description
Author: Kenneth W. Goodson
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 52
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Book Description
"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.
