Static Stability Characteristics of a Delta-winged Configuration with a Canard Control and Nacelles at Mach Numbers from 0.25 to 3.50 PDF Download
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Author: LeRoy S. Fletcher
Publisher:
ISBN:
Category :
Languages : en
Pages : 108
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Author: LeRoy S. Fletcher
Publisher:
ISBN:
Category :
Languages : en
Pages : 108
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 68
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Author:
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ISBN:
Category :
Languages : en
Pages : 714
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Author: C. Ernest Hedstrom
Publisher:
ISBN:
Category :
Languages : en
Pages : 62
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Author: Herman S. Fletcher
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 48
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Book Description
Methods presented in five different publications have been used to estimate the low-speed stability derivatives of two unpowered airplane configurations. One configuration had unswept lifting surfaces, the other configuration was the D-558-II swept-wing research airplane. The results of the computations were compared with each other, with existing wind-tunnel data, and with flight-test data for the D-558-II configuration to assess the relative merits of the methods for estimating derivatives. The results of the study indicated that, in general, for low subsonic speeds, no one text appeared consistently better for estimating all derivatives.
Author: M. Leroy Spearman
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ISBN:
Category :
Languages : en
Pages : 51
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Author:
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Category :
Languages : en
Pages : 36
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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: Victor L. Peterson
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 31
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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 vertical tail, and a Sears-Haack body. The hinge line of the canard was in the extended chord plane of the wing, 1.15 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: Clarence D. Cone (Jr.)
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 76
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