Aerodynamic Characteristics of a 45 Degree Swept-back Wing with Aspect Ratio of 3.5 and NACA 2S-50(05)-50(05) Airfoil Sections PDF Download
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Author: Anthony J. Proterra
Publisher:
ISBN:
Category :
Languages : en
Pages : 16
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Book Description
Author: Anthony J. Proterra
Publisher:
ISBN:
Category :
Languages : en
Pages : 16
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Book Description
Author: William C. Sleeman
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 36
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Book Description
Author: Boyd C. Myers
Publisher:
ISBN:
Category : Airplane
Languages : en
Pages : 36
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Book Description
This paper presents the results of the investigation of a wing-alone and wing-fuselage configuration employing a wing with the quarter-chord line swept back 45 degrees, with aspect ratio 4, taper ratio 0.3, 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 were also obtained for these configurations and are presented for a range of tail heights at one tail length. In order to expedite the 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: William C. Sleeman
Publisher:
ISBN:
Category :
Languages : en
Pages : 32
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Author: Joseph Weil
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 28
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Book Description
As part of an NACA research program, a series of wing-body combinations are being investigated in the Langley high-speed 7- by 10-foot tunnel up to a Mach number of 1.18 utilizing the transonic bump.
Author: Kenneth W. Goodson
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 34
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Book Description
This paper presents the results of the investigation of a wing-alone and a wing-fuselage configuration employing a wing with the quarter-chord line swept back 45 degrees, aspect ratio 6, taper ratio 0.6, 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 configurations and are presented for a range of tail heights at one tail length. In order to expedite the publishing of these data, only a brief analysis is included.
Author: Arvo A. Luoma
Publisher:
ISBN:
Category :
Languages : en
Pages : 59
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Author: Robert H. Neely
Publisher:
ISBN:
Category :
Languages : en
Pages : 40
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Author: William D. Morrison
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 38
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Book Description
An aerodynamic investigation has been conducted in the Langley high-speed 7- by 10-foot tunnel to determine the effects of taper-in-thickness on the aerodynamics characteristics of wings having 35 and 45 degrees of sweep-back, aspect ratio 6, and taper ratio 0.60. The wings were tapered from NACA 65A009 airfoil sections at the root chord to NACA 65A003 airfoil sections at the tip chord. The test Mach number range was from 0.60 to 1.14 at a Reynolds number of the order of 500,000.
