Aerodynamic Characteristics at Transonic Speeds of a Tapered 45 Degrees Sweptback Wing of Aspect Ratio 3 Having a Full-span Flap-type Control PDF Download
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Author: Vernard E. Lockwood Publisher: ISBN: Category : Aerodynamics Languages : en Pages : 35
Book Description
The aerodynamic characteristics in pitch and the control characteristics of a wing-flap combination have been determined for a wing having a quarter-chord line sweep of 45.58 degrees, an aspect ratio of 3, a taper ratio of 0.5, and an NACA 64A010 airfoil section measured in a plane at an angle of 45 degrees to the plane of symmetry. The wing employed a 25.4-percent-chord full-span plain flap-type control with a removable seal so that the effects of a relatively small gap could be determined. The investigation covered a Mach number range from 0.6 to 1.17 at angles of attack of 0, 4, and 8 degrees through a control-surface deflection range from -27 degrees to approximately 5 degrees. These data were obtained from the Langley high-speed 7- by 10-foot-tunnel transonic bump.
Author: Vernard E. Lockwood Publisher: ISBN: Category : Aerodynamics Languages : en Pages : 35
Book Description
The aerodynamic characteristics in pitch and the control characteristics of a wing-flap combination have been determined for a wing having a quarter-chord line sweep of 45.58 degrees, an aspect ratio of 3, a taper ratio of 0.5, and an NACA 64A010 airfoil section measured in a plane at an angle of 45 degrees to the plane of symmetry. The wing employed a 25.4-percent-chord full-span plain flap-type control with a removable seal so that the effects of a relatively small gap could be determined. The investigation covered a Mach number range from 0.6 to 1.17 at angles of attack of 0, 4, and 8 degrees through a control-surface deflection range from -27 degrees to approximately 5 degrees. These data were obtained from the Langley high-speed 7- by 10-foot-tunnel transonic bump.
Author: Lawrence D. Guy Publisher: ISBN: Category : Aerodynamics, Supersonic Languages : en Pages : 52
Book Description
A wind-tunnel investigation has been made of two unswept, partial-span, flap-type controls (differing only in hinge-line location) mounted on a 60 degree delta wing. One control was unbalanced and the other has a 100-percent overhang balance. Control hinge moments as well as aerodynamic characteristics of the complete wing-body combination were obtained for control deflections from 0 to 40 degrees over an angle-of-attack range of plus or minus 12 degrees at Mach numbers from 0.75 to 1.96. Reynolds numbers varied between 2,200,000 and 2,200,000. Expressions derived from linear theory for the hinge-moment coefficient due to angle of attack for unswept partial-span controls (which extend neither to the wing tip nor to the wing center line) on triangular wings having subsonic leading edges are given in an appendix.
Author: Jack F. Runckel Publisher: ISBN: Category : Aerodynamic load Languages : en Pages : 104
Book Description
An investigation at transonic speeds of the loading over a 45 degree sweptback wing having an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections has been conducted in the Langley16-foot transonic tunnel. Pressure measurements on the wing-body combination were obtained at angles of attack from 0 to 26 degrees at Mach numbers from 0.80 to 0.98 and from 0 to about 12 degrees at Mach numbers from 1.00 to 1.05. Reynolds number, based on the wing mean aerodynamic chord, varied from 7,000,000 to 8,500,000 over the test Mach number range.
Author: Douglas R. Lord Publisher: ISBN: Category : Aerodynamics Languages : en Pages : 52
Book Description
An investigation has been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.61 and 2.01 to determine the aerodynamic characteristics of a spoiler-slot-deflector control on a 45 degree sweptback wing having an aspect ratio of 3.5, a taper ratio of 0.3, and an NACA 65A005 airfoil section. The model was equipped with a 15-percent-chord spoiler-slot-deflector extending from 13 o 78 percent of the wing semispan. The spoiler and deflector were hinged along the 60- and 75-percent-chord lines, respectively. Tests were made at a Reynolds number of 3,000,000 (based on the mean aerodynamic chord of the wing) and covered ranges of angles of attack from -3 to 15 degrees, spoiler projections from 0 to 8.0 percent chord, and deflector projections from 0 to 7.6 percent chord.
Author: William D. Morrison Publisher: ISBN: Category : Aerodynamics, Transonic Languages : en Pages : 22
Book Description
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.
Author: Vernard E. Lockwood
Author: Vernard E. Lockwood
Author: Vernard E. Lockwood
Author: Vernard E. Lockward
Author: Lawrence D. Guy
Author: Jack F. Runckel
Author: Douglas R. Lord
Author: William D. Morrison
Author: Vernard E. Lockwood
Author: Joseph E. Fikes
Author: James M. Watson