Download or read book Aerodynamic Characteristics of a Wing with Quarter chord Line Swept Back 45 Degrees Aspect Ratio 6 Taper Ratio 0 6 and NACA 65A009 Airfoil Section written by Kenneth P. Spreemann and published by . This book was released on 1950 with total page 33 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper presents the results of the investigation of a wing-along and wing-fuselage configurations employing a wing with the quarter-chord line swept back 45 degrees, aspect ratio 6, taper ratio 0.6, and an NACA 65A009 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 probable tail locations were obtained for these configurations and are presented for a range of tail heights at one tail length.

Download or read book Aerodynamic Characteristics of a Wing with Quarter chord Line Swept Back 35 Aspect Ratio 6 Taper Ratio 0 6 and NACA 65A006 Airfoil Section written by William C. Sleeman and published by . This book was released on 1949 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Characteristics of a Wing with Quarter chord Line Swept Back 45 Degrees Aspect Ratio 4 Taper Ratio 0 3 and NACA 65A006 Airfoil Section written by Boyd C. Myers and published by . This book was released on 1949 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.

Download or read book Aerodynamic Characteristics of a Wing with Quarter chord Line Swept Back 35 Degrees Aspect Ratio 6 Taper Ratio 0 6 and NACA 65A006 Airfoil Section written by William C. Sleeman and published by . This book was released on 1949 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Characteristics of a Wing with Quarter chord Line Swept Back 45 Degrees Aspect Ratio 6 Taper Ratio 0 6 and NACA 65A006 Airfoil Section written by Kenneth W. Goodson and published by . This book was released on 1949 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.

Download or read book Aerodynamic Characteristics of a Wing with Quarter chord Line Swept Back 45 Degrees Aspect Ratio 4 Taper Ratio 0 6 and NACA 65A006 Airfoil Section written by Joseph Weil and published by . This book was released on 1949 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.

Download or read book Aerodynamic Characteristics of a Wing with Quarter chord Line Swept Back 60 Degrees Aspect Ratio 4 Taper Ratio 0 6 and NACA 65A006 Airfoil Section Transonic bump Method written by Thomas J. Jr King and published by . This book was released on 1949 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Characteristics of a Wing with Quarter chord Line Swept Back 60 Degrees Aspect Ratio 2 Taper Ratio 0 6 and NACA 65A006 Airfoil Section written by Boyd C. Myers and published by . This book was released on 1950 with total page 31 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper presents the results of the investigation of a wing-alone and a wing-fuselage configuration employing a wing with quarter-chord line swept back 60 degrees, aspect ratio 2, taper ratio 0.6, and an NACA 65A006 airfoil section. The results are presented as lift, drag, pitching-moment and bending-moment coefficients for both configurations. In addition, effective downwash angles and point dynamic pressures for a range of tail heights at a probable tail length are presented for the two configurations investigated.

Download or read book Aerodynamic Characteristics of a Wing with Quarter chord Line Swept Back 35 Degrees Aspect Ratio 4 Taper Ratio 0 6 and NACA 65A006 Aifoil Section Transonic bump Method written by William C. Jr Sleeman and published by . This book was released on 1949 with total page 29 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Characteristics of a Wing with Quarter chord Line Swept Back 35 Degrees Aspect Ratio 4 Taper Ratio 0 6 and NACA 65A006 Airfoil Section written by William C. Sleeman and published by . This book was released on 1949 with total page 29 pages. Available in PDF, EPUB and Kindle. Book excerpt: This 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.

Download or read book Aerodynamic Characteristics of Tapered Wings Having Aspect Ratios of 4 6 and 8 Quarter chord Lines Swept Back 45 Degrees and NACA 63 sub 1 A012 Airfoil Sections written by Edward C. Polhamus and published by . This book was released on 1951 with total page 23 pages. Available in PDF, EPUB and Kindle. Book excerpt: As part of a transonic research program conducted by the National Advisory Committee for Aeronautics, a series of wings is being investigated in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0.70 to 1.15 by use of the transonic-bump technique.

Download or read book Aerodynamic Characteristics of a Wing with Quarter chord Swept Back 60 Degrees Aspect Ratio 4 Taper Ratio 0 6 and NACA 65A006 Airfoil Section written by Thomas J. King and published by . This book was released on 1949 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper presents the results of the investigation of a wing-alone and a wing-fuselage configuration employing a wing with quarter-chord line swept back 60 degrees, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section. The results are presented as lift, drag, pitching-moment, and bending moment coefficients for both configurations. The effect of a wing fence on the wing-fuselage characteristics was also investigated. In addition, effective downwash angles and point dynamic pressures for a range of tail heights at a probable tail length are presented for the two configurations investigated. Only a brief analysis is given in order to facilitate the publishing of the data.

Download or read book Aerodynamic Characteristics of Four Wings of Sweepback Angles 0 Degrees 35 Degrees 45 Degrees and 60 Degrees NACA 65A006 Airfoil Section Aspect Ratio 4 and Taper Ratio 0 6 in Combination with a Fuselage at High Subsonic Mach Numbers and at a Mach Number of 1 2 written by Arvo A. Luoma and published by . This book was released on 1951 with total page 59 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Characteristics at Transonic Speeds of a Wing Having 45 Degrees Sweep Aspect Ratio 8 Taper Ratio 0 45 and Airfoil Sections Varying from the NACA 63A010 Section at the Root to the NACA 63A006 Section at the Tip written by William D. Jr Morrison and published by . This book was released on 1952 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Characteristics of a 45 Degree Swept back Wing with Aspect Ratio of 3 5 and NACA 2S 50 05 50 05 Airfoil Sections written by Anthony J. Proterra and published by . This book was released on 1947 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Characteristics of a Wing with Unswept Quarter chord Line Aspect Ratio 2 Taper Ratio 0 78 and NACA 65A004 Airfoil Section written by Edward C. Polhamus and published by . This book was released on 1950 with total page 17 pages. Available in PDF, EPUB and Kindle. Book excerpt: The aerodynamic characteristics of a low-aspect-ratio wing have been investigated in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0.60 to 1.17 by use of the transonic bump technique. The results include lift, drag, pitching-moment, and root bending moment for a wing having an unswept quarter-chord line, aspect ratio 2, taper ratio 0.78, and an NACA 65A004 airfoil section.

Download or read book Aerodynamic Characteristics at Transonic Speeds of a Wing Having a 45 Degree Sweep Aspect Ratio 8 Taper Ratio 0 45 and Airfoil Sections Varying from the NACA 63A010 Section at the Root to the NACA 63A006 Section at the Tip written by William D. Morrison and published by . This book was released on 1952 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been conducted in the Langley High-Speed 7- by 10-foot tunnel to determine the transonic aerodynamic characteristics of a wing having a spanwise variation in thickness ratio. The wing investigated had 45 degrees of sweepback, aspect ratio 8, taper ratio of 0.45, and airfoil sections tapered from an NACA 63A010 section at the root chord to an NACA 63A006 section at the tip chord. The test Mach number range was from 0.60 to 1.05 at Reynolds numbers of the order of 500,000.