Wing-flow Measurements of Longitudinal Stability and Control Characteristics of a Canard Airplane Configuration with a 45 Degree Sweptback Wing and a Triangular All-movable Control Surface PDF Download
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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: 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: Harold L. Crane
Publisher:
ISBN:
Category :
Languages : en
Pages : 53
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Book Description
Author: M. Leroy Spearman
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
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Author: William R. Bates
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 38
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
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Book Description
Author: John W. Draper
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 43
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Book Description
An investigation has been made of the low-speed static stability characteristics of a canard model with a 45 degree sweptback wing and a 60 degree triangular horizontal control surface. The model had practically no allowable center-of-gravity range because of longitudinal instability that occurred at moderate and high lift coefficients with horizontal-control-surface incidences of 10 degrees or less. The horizontal control surface produced a sidewash which, at an incidence of 15 degrees at angles of attack greater than 7 degrees, was strong enough to make the model directionally stable with the vertical tail off. This sidewash caused a vertical tail mounted on the fuselage to be destabilizing at angles of attack above 11 degrees. Twin vertical tails mounted at the wing tips did not produce a similar destabilizing effect because they were located outside the sidewash field.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 456
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Author: Clarence D. Cone (Jr.)
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 76
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Author: A. James Vitale
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 24
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Book Description
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: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 448
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Book Description
