Aerodynamic Characteristics of a Delta Wing with Leading Edge Swept Back 45 Degrees, Aspect Ratio 4, and NACA 65A006 Airfoil Section PDF Download
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Author: William C. Sleeman
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 34
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Book Description
This paper presents the results of the investigation of wing-alone and wing-fuselage combination employing a delta wing having 45 degree sweepback of the leading edge, aspect ratio 4, and an NACA 65A006 airfoil section. Lift, drag, pitching moment, and root bending moment were obtained for these configurations. In addition, effective downwash angles and dynamic-pressure characteristics in the region of a probable tail location also were obtained for these configurations, and are presented for a range of tail heights at one tail length. In order to expedite publishing of these data, only a brief analysis is included.
Author: William C. Sleeman
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 34
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Book Description
This paper presents the results of the investigation of wing-alone and wing-fuselage combination employing a delta wing having 45 degree sweepback of the leading edge, aspect ratio 4, and an NACA 65A006 airfoil section. Lift, drag, pitching moment, and root bending moment were obtained for these configurations. In addition, effective downwash angles and dynamic-pressure characteristics in the region of a probable tail location also were obtained for these configurations, and are presented for a range of tail heights at one tail length. In order to expedite publishing of these data, only a brief analysis is included.
Author: Robert W. Dunning
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 24
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Author: Anthony J. Proterra
Publisher:
ISBN:
Category :
Languages : en
Pages : 16
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Author: John P. Mugler
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 44
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Book Description
An investigation was conducted in the Langley 8-foot transonic tunnel to determine the aerodynamic characteristics of a thin 60 degree delta wing with two leading-edge modifications (conical leading-edge camber and leading-edge droop) in combination with bodies with and without body indentation in accordance with the transonic-area-rule concept. The tests covered a Mach number range from 060 to 1.15 and an angle-of-attack range from -4 to 20 degrees at a Reynolds number of about 3,000,000 based on the wing mean aerodynamic chord. The wing had an aspect ratio of 2.31, a taper ratio of 0, and, without modifications, had NACA 65A003 airfoil sections parallel to the model plane of symmetry.
Author: Thomas J. Jr King
Publisher:
ISBN:
Category :
Languages : en
Pages : 32
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Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 508
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Author: Robert S. Osborne
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 20
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Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 442
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Author: William C. Sleeman
Publisher:
ISBN:
Category :
Languages : en
Pages : 32
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Author: Arvo A. Luoma
Publisher:
ISBN:
Category :
Languages : en
Pages : 59
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