Aerodynamic Characteristics of a 45 Degree Swept-back Wing with Aspect Ratio of 3.5 and NACA 2S-50(05)-50(05) Airfoil Sections
Author: Anthony J. Proterra
Publisher:
Published: 1947
Total Pages: 16
ISBN-13:
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Author: Anthony J. Proterra
Publisher:
Published: 1947
Total Pages: 16
ISBN-13:
DOWNLOAD EBOOKAuthor: William C. Sleeman
Publisher:
Published: 1949
Total Pages: 36
ISBN-13:
DOWNLOAD EBOOKAuthor: Boyd C. Myers
Publisher:
Published: 1949
Total Pages: 36
ISBN-13:
DOWNLOAD EBOOKThis 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:
Published: 1949
Total Pages: 32
ISBN-13:
DOWNLOAD EBOOKAuthor: William Solomon
Publisher:
Published: 1953
Total Pages: 44
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DOWNLOAD EBOOKAuthor: Arvo A. Luoma
Publisher:
Published: 1951
Total Pages: 59
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DOWNLOAD EBOOKAuthor: Kenneth W. Goodson
Publisher:
Published: 1949
Total Pages: 34
ISBN-13:
DOWNLOAD EBOOKThis 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: Joseph Weil
Publisher:
Published: 1949
Total Pages: 28
ISBN-13:
DOWNLOAD EBOOKAs 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: William C. Sleeman
Publisher:
Published: 1949
Total Pages: 29
ISBN-13:
DOWNLOAD EBOOKThis paper presents the results of the investigation of a wing-alone and a wing-fuselage combination employing a wing with the quarter-chord line swept back 35 degrees, aspect ratio 4, taper ratio 0.6, and an NACA 65A006 airfoil section. Lift, drag, pitching moment, and root bending moment were obtained for the wing-alone and wing-body configurations. 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 publishing of these data, only a brief analysis is included.
Author: Robert H. Neely
Publisher:
Published: 1947
Total Pages: 40
ISBN-13:
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