Lateral Control Investigation Of Flap Type Controls On A Wing With Quarter Chord Line Sweptback 35 Aspect Ratio 4 Taper Ratio 0 6 And Naca 65a006 Airfoil Section
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Lateral control Investigation of Flap type Controls on a Wing with Quarter chord Line Sweptback 35 Aspect Ratio 4 Taper Ratio 0 6 and NACA 65A006 Airfoil Section
Author | : Robert F. Thompson |
Publsiher | : Unknown |
Total Pages | : 28 |
Release | : 1950 |
Genre | : Aerofoils |
ISBN | : UOM:39015086490557 |
Download Lateral control Investigation of Flap type Controls on a Wing with Quarter chord Line Sweptback 35 Aspect Ratio 4 Taper Ratio 0 6 and NACA 65A006 Airfoil Section Book in PDF, Epub and Kindle
This paper presents the results of an investigation to determine the control-effectiveness characteristics of 30-percent-chord flap-type control surfaces of various spans on a semispan wing-fuselage model. The wing of the mode had 35 degrees of sweepback of the quarter chord, an aspect ratio of 4.0, a taper ratio of 0.6, and an NACA 65A006 airfoil section parallel to the free stream. Lift, rolling moments, and pitching moments were obtained for several angle of attack throughout a small range of control-surface deflections. Most of the data are presented as control-effectiveness parameters which show their variation with Mach number.
Index of NACA Technical Publications
Author | : United States. National Advisory Committee for Aeronautics |
Publsiher | : Unknown |
Total Pages | : 242 |
Release | : 1955 |
Genre | : Aeronautics |
ISBN | : STANFORD:36105024165651 |
Download Index of NACA Technical Publications Book in PDF, Epub and Kindle
A Selected Listing of NASA Scientific and Technical Reports for
Author | : Anonim |
Publsiher | : Unknown |
Total Pages | : 750 |
Release | : 1949 |
Genre | : Aeronautics |
ISBN | : UVA:X004173285 |
Download A Selected Listing of NASA Scientific and Technical Reports for Book in PDF, Epub and Kindle
Aerodynamic Characteristics of a Wing with Quarter chord Line Swept Back 35 Aspect Ratio 6 Taper Ratio 0 6 and NACA 65A006 Airfoil Section
Author | : William C. Sleeman |
Publsiher | : Unknown |
Total Pages | : 36 |
Release | : 1949 |
Genre | : Aerodynamics, Transonic |
ISBN | : UOM:39015086464610 |
Download Aerodynamic Characteristics of a Wing with Quarter chord Line Swept Back 35 Aspect Ratio 6 Taper Ratio 0 6 and NACA 65A006 Airfoil Section Book in PDF, Epub and Kindle
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
Author | : Boyd C. Myers |
Publsiher | : Unknown |
Total Pages | : 36 |
Release | : 1949 |
Genre | : Airplane |
ISBN | : UOM:39015086490524 |
Download 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 Book in PDF, Epub and Kindle
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.
Aerodynamic Characteristics of a Delta Wing with Leading Edge Swept Back 45 Degrees Aspect Ratio 4 and NACA 65A006 Airfoil Section
Author | : William C. Sleeman |
Publsiher | : Unknown |
Total Pages | : 34 |
Release | : 1949 |
Genre | : Aerofoils |
ISBN | : UOM:39015086464503 |
Download Aerodynamic Characteristics of a Delta Wing with Leading Edge Swept Back 45 Degrees Aspect Ratio 4 and NACA 65A006 Airfoil Section Book in PDF, Epub and Kindle
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.
Transonic Wind tunnel Investigation of the Effects of Sweepback and Thickness Ratio on the Wing Loads of a Wing body Combination of Aspect Ratio 4 and Taper Ratio 0 6
Author | : Robert J. Platt |
Publsiher | : Unknown |
Total Pages | : 50 |
Release | : 1955 |
Genre | : Aerodynamic load |
ISBN | : UOM:39015095100858 |
Download Transonic Wind tunnel Investigation of the Effects of Sweepback and Thickness Ratio on the Wing Loads of a Wing body Combination of Aspect Ratio 4 and Taper Ratio 0 6 Book in PDF, Epub and Kindle
A transonic investigation of the effects of sweepback and thickness ratio on the wing loads of a wing in the presence of a body has been made in the Langley 8-foot transonic pressure tunnel. The tests covered wings with a thickness ratio of 6 percent for sweepback angles of 0, 25, and 45 degrees and a thickness ratio of 4 percent for an unswept wing.
Investigation of the Effects of Leading edge Chord extensions and Fences in Combination with Leading edge Flaps on the Aerodynamic Characteristics at Mach Numbers from 0 40 to 0 93 of a 45 Degree Sweptback Wing of Aspect Ratio 4
Author | : Kenneth P. Spreemann |
Publsiher | : Unknown |
Total Pages | : 644 |
Release | : 1957 |
Genre | : Airplanes |
ISBN | : STANFORD:36105024832128 |
Download Investigation of the Effects of Leading edge Chord extensions and Fences in Combination with Leading edge Flaps on the Aerodynamic Characteristics at Mach Numbers from 0 40 to 0 93 of a 45 Degree Sweptback Wing of Aspect Ratio 4 Book in PDF, Epub and Kindle
This investigation was made to determine the effects of 6 degree full-span and 3 degree partial-span leading-edge flaps in combination with chord-extensions or fences on the aerodynamic characteristics of a wing-fuselage configuration with a 45 degree sweptback wing of aspect ratio 4, taper ratio 0.3, and NACA 65A006 airfoil sections. The investigation was made in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0.40 to 0.93 and an angle-of-attack range of about -2 degrees to 24 degrees. Lift, drag, and pitching-moment data were obtained for all configurations. From overall considerations of stability and performance it appears that with the model of this investigation the 6 degree full-span leading-edge flaps in combination with the chord-extension over the outboard 35 percent of the span, with or without leading-edge camber, would be the most desirable configuration.