Longitudinal Stability and Control Characteristics at Mach Numbers of 1.41 and 2.01 of a 67 Degree Swept-wing Airplane Configuration with Canard Control Surfaces PDF Download
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Author: M. Leroy Spearman
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
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Author: M. Leroy Spearman
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
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Author: Harold L. Crane
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 53
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Book Description
Measurements of the longitudinal stability and control characteristics of a canard airplane configuration have been made by the wing-flow method. The distinguishing features of this configuration in addition to the unconventional wing-stabilizer arrangement are the triangular plan form of the all-movable longitudinal control surface, the 45 degree sweptback wing of aspect ratio 4.1, and the slender body of fineness ratio 13.5. The investigation included measurements of lift, pitching moment, and rolling moment of the semispan model, with control settings between -4 degrees and 16 degrees and with the control surface removed. In some cases the angle-of-attack range was as great as from approximately -10 to 30 degrees. Approximate measurements of chord force were made at one stabilizer incidence. The Mach number range covered was from 0.55 to 1.14 at Reynolds numbers of the order of 400,000.
Author: Gerald V. Foster
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 38
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Author: John W. Boyd
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 48
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Author: Harold L. Crane
Publisher:
ISBN:
Category :
Languages : en
Pages : 53
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![Longitudinal Stability and Control Characteristics at Mach Numbers from 0.70 to 2.22 of Triangular Wing Configuration Equipped with Canard Control, Trailing-edge Flap Control, Or Cambered Forebody [with List of References] PDF](https://books.google.com/books/content/images/frontcover/YHSVtAEACAAJ?fife=w80-h100)
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 39
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Author: Victor L. Peterson
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 29
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The results of an investigation of the static longitudinal stability and control characteristics of a canard airplane configuration are presented without analysis for the Mach number range from 0.70 to 2.22. The configuration consisted of an aspect ratio 3.1 unswept wing, an aspect ratio 3.0 unswept canard, a low aspect ratio vertical tail, and a Sears-Haack body. The hinge line of the canard was in the extended chord plane of the wing, 1.33 wing mean aerodynamic chords ahead of the reference center of moments. The ratio of the area of the exposed canard panels to the total area of the wing is 8.1 percent. Data are presented for various combinations of the canard, wing, and vertical tail for an angle-of-attack range from -6 to 18 degrees. The canard deflection angles ranged from 0 to 20 degrees.
Author: A. James Vitale
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 24
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A flight investigation has been conducted to determine the longitudinal stability, lift, and drag characteristics at transonic speeds of a rocket-powered model of a canard configuration having a 45 degree swept-back wing of aspect ratio 6.0, taper ratio of 0.6, and NACA 65A009 airfoil section. The canard surface had an aspect ratio of 4.0 and 45 degrees of sweepback. The variations with Mach number of lift, drag, and longitudinal stability for the canard configuration are compared with a tailless and a conventional or tail-last model having the same wing.
Author: Jim A. Penland
Publisher:
ISBN:
Category : Aerodynamic measurements
Languages : en
Pages : 150
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