Wind-tunnel Investigation of Longitudinal Aerodynamic Characteristics of Three Propeller-driven VTOL Configurations in the Transition Speed Range, Including Effects of Ground Proximity PDF Download
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Author: Richard E. Kuhn
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 134
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Book Description
Author: Richard E. Kuhn
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 134
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Book Description
Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 448
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Book Description
Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 494
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Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 860
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 544
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Book Description
Author: Kenneth W. Goodson
Publisher:
ISBN:
Category : Flaps (Airplanes)
Languages : en
Pages : 116
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 296
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Author: Kenneth W. Goodson
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 52
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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.
Author:
Publisher:
ISBN:
Category : Short take-off and landing aircraft
Languages : en
Pages : 380
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