Low-speed Investigation of a Thin, Faired, Double-wedge Airfoil Section with Nose Flaps of Various Chords PDF Download
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Author: Leonard M. Rose
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 22
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Book Description
A faired, double-wedge airfoil section was investigated with plain nose flaps of 12, 16, 20, and 25 percent of the airfoil chord. Section lift, drag, and pitching-moment data were obtained at Reynolds number of 5.8 million and a Mach number of 0.17.
Author: Leonard M. Rose
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 22
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Book Description
A faired, double-wedge airfoil section was investigated with plain nose flaps of 12, 16, 20, and 25 percent of the airfoil chord. Section lift, drag, and pitching-moment data were obtained at Reynolds number of 5.8 million and a Mach number of 0.17.
Author: Leonard M. Rose
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 28
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Book Description
A faired, double-wedge airfoil section, 4.23 percent thick, was investigated with plain nose and trailing-edge flaps. The nose flap was 0.16 chord of the airfoil and the trailing-edge flap was 0.25 chord of the airfoil. Section lift, drag, and pitching-momnet data are presented for a Reynolds number of 5,800,000 which corresponded to a Mach number of 0.17.
Author: Leonard M. Rose
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 27
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Book Description
The stalling characteristics of a 4.23-percent-thick, faired, double-wedge airfoil section with and without nose flap were investigated. Flap chords of 12, 16, 20, and 25 percent of the airfoil chord were tested. Results of force and pressure-distribution measurements as well as studies of the flow above the airfoil are presented for a Reynolds number of 5,800,000 and a Mach number of 0.17.
Author: Manuel Stein
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 694
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Book Description
A small-deflection theory that takes into account deformations due to transverse shear is presented for the elastic-behavior analysis of orthotropic plates of constant cylindrical curvature, with considerations of buckling included. The theory is applicable primarily to sandwich construction.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 456
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Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 926
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Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 498
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Author: Robert E. Dannenberg
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 678
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Book Description
Tunnel-wall corrections for the induced upwash velocity for a swept wing completely spanning a rectangular wind tunnel are included in the appendix.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 750
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Book Description
Author: College of Aeronautics (Cranfield, England)
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
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Book Description
