Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Aerodynamic Characteristics Of A Wing With Quarter Chord Line Swept Back 35c Aspect Ratio 6 Taper Ratio 06 And Naca 65a006 Airfoil Section PDF full book. Access full book title Aerodynamic Characteristics Of A Wing With Quarter Chord Line Swept Back 35c Aspect Ratio 6 Taper Ratio 06 And Naca 65a006 Airfoil Section.
| Author | : William C. Sleeman |
| Publisher | : |
| Total Pages | : 36 |
| Release | : 1949 |
| Genre | : Aerodynamics, Transonic |
| ISBN | : |
| Author | : William C. Sleeman |
| Publisher | : |
| Total Pages | : 32 |
| Release | : 1949 |
| Genre | : |
| ISBN | : |
| Author | : Boyd C. Myers |
| Publisher | : |
| Total Pages | : 36 |
| Release | : 1949 |
| Genre | : Airplane |
| ISBN | : |
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 | : Kenneth W. Goodson |
| Publisher | : |
| Total Pages | : 34 |
| Release | : 1949 |
| Genre | : Aerofoils |
| ISBN | : |
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 | : Thomas J. Jr King |
| Publisher | : |
| Total Pages | : 32 |
| Release | : 1949 |
| Genre | : |
| ISBN | : |
| Author | : William C. Jr Sleeman |
| Publisher | : |
| Total Pages | : 29 |
| Release | : 1949 |
| Genre | : |
| ISBN | : |
| Author | : William C. Sleeman |
| Publisher | : |
| Total Pages | : 34 |
| Release | : 1949 |
| Genre | : Aerofoils |
| ISBN | : |
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 | : |
| Total Pages | : 29 |
| Release | : 1949 |
| Genre | : Aerodynamics, Transonic |
| ISBN | : |
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.
| Author | : Boyd C. Myers |
| Publisher | : |
| Total Pages | : 31 |
| Release | : 1950 |
| Genre | : Airplanes |
| ISBN | : |
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.
| Author | : Joseph Weil |
| Publisher | : |
| Total Pages | : 28 |
| Release | : 1949 |
| Genre | : Aerofoils |
| ISBN | : |
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.
