High-subsonic Damping-in-roll Characteristics of a Wing with the Quarter-chord Line Swept Back 35 Degrees and with Aspect Ratio 3 and Taper Ratio 0.6 PDF Download
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Author: Boyd C. II. Myers
Publisher:
ISBN:
Category :
Languages : en
Pages : 21
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Book Description
Author: Boyd C. II. Myers
Publisher:
ISBN:
Category :
Languages : en
Pages : 21
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Book Description
Author: William B. Kemp
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 32
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Book Description
Author: Richard E. Kuhn
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 28
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Book Description
The damping-in-roll characteristics of three wings with an aspect ratio of 4, a taper ratio of 0.6, sweep angles of 3.6, 32.5, and 46.7 degrees at quarter-chord line, and with the NACA 65A006 section have been determined through the Mach number range from 0.4 to 0.91 and angle-of-attack range from 0 to 6.5 degrees in the Langley high-speed 7- by 10-foot tunnel by the free-roll method. The results indicated that the increase in magnitude of the damping-in-roll coefficient with Mach number and the decrease with sweep angle, at low angles of attack, agreed well with the theoretical variations. The damping coefficient increased markedly with angle of attack (in the test range) particularly at the higher Mach numbers investigated.
Author: James W. Wiggins
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 56
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Book Description
An investigation was performed in the Langley high-speed 7- by 10-foot tunnel in order to determine the rolling derivatives for swept-wing-body configurations at angles of attack from 0 degrees to 13 degrees and at high subsonic Mach numbers. The wings had sweep angles of 3.6 degrees, 32.6 degrees, 45 degrees, and 60 degrees at the quarter-chord line, an aspect ratio of 4, a taper ratio of 0.6, and an NACA 65A006 airfoil section parallel to the free stream. The results indicate a reduction in the damping-in-roll derivative at the higher test angles of attack. Of the wings tested, instability of the damping-in-roll derivative was experienced over the largest ranges of angle of attack and Mach number for the 32.6 sweptback wing.
Author: Edward C. Polhamus
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 90
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Book Description
A summary and analysis has been made of results obtained in a systematic research program concerned with the effects of wing sweep, aspect ratio, taper ratio, and dihedral on the rolling moment due to sideslip characteristics of wing-fuselage configurations up to Mach numbers of about 0.95. Other test results are presented to show trends of rolling moment due to sideslip with Mach number for a few wings in the transonic and supersonic speed range.
Author: Richmond P. Boyden
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 44
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Book Description
Author: Frank S. Malvestuto
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 48
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Book Description
Design curves are presented which permit rapid estimation of the lift-curve slope and damping-in-roll derivative for given values of aspect ratio, taper ratio, Mach number, and leading edge sweep.
Author: Vernard E. Lockwood
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 23
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Book Description
The damping-in-roll characteristics of three wings having an aspect ratio of 4, a taper ratio of 0.6, and NACA 65A006 airfoil section, and sweep angles of 0, 35, and 45 degrees have been determined through a Mach number range from 0.6 to 1.15 and an angle-of-attack range from 0 to approximately 7 degrees. The data were obtained from the Langley 7- by 10-foot tunnel transonic bump by utilizing the twisted-wing technique.
Author: Edward C. Polhamus
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 26
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Book Description
A method of modifying existing correction factors of lifting-surface theory to account approximately for the effects of sweep has been derived, and these factors have been applied to existing lifting-line theories for the lift and damping in roll of swept wings. A comparison with experimental data in the low-speed and low lift range indicated good agreement for wings of any plan form. If the Glauert-Prandtl transformation is used, the formulas obtained can be applied to swept wings at subsonic speeds below the critical speed.
Author: M. Leroy Spearman
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 34
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Book Description
An investigation has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel to determine the effects of wing and horizontal-tail vertical location on the aerodynamic characteristics in sideslip at various angles of attack for a supersonic airplane configuration at Mach numbers of 1.41 and 2.01. The basic model was equipped with a wing and horizontal tail, each having 45 degree sweep and an aspect ratio of 4. The wing had a taper ratio of 0.2 and NACA 65A004 sections; the horizontal tail had a taper ratio of 0.4 and NACA 65A006 sections.
