The Effects of Wing Plan Form on the Static Longitudinal Aerodynamic Characteristics of a Flat-top Hypersonic Aircraft at Mach Numbers from 0.6 to 1.4 PDF Download
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Author: Stuart L. Treon
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 36
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Author: Stuart L. Treon
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 36
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1280
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Author: Albert G. Few
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 80
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Book Description
The drag due to lift increases with increasing sweep through the Mach number range. Some increase in bag due to lift is evident decrease in taper ratio for wings having 300of sweep through most of the speed range.
Author: Royce L. McKinney
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 52
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Author: J. T. Best (Jr.)
Publisher:
ISBN:
Category : Drag (Aerodynamics)
Languages : en
Pages : 122
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Author: Odell A. Morris
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 32
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Author: John R. Krouse
Publisher:
ISBN:
Category :
Languages : en
Pages : 28
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Wind tunnel tests were conducted at a Mach number of 9.45 to determine the aerodynamic characteristics of several conceptual hypersonic aircraft configurations consisting of various half-cone-cylinder bodies and double-delta wings. Effects of body volume, wing planform, and wing-tip deflection on static directional stability were determined. In addition, the effects of wing thickness on the aerodynamic efficiency were obtained. Decreasing body volume, extending the trailing edges, and deflecting the wing tips (toward or away from the fuselage) were all directionally stabilizing. Decreasing wing thickness significantly increased maximum untrimmed lift-to-drag ratios.
Author: James L. Dillon
Publisher:
ISBN:
Category : Hypersonic planes
Languages : en
Pages : 68
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Author: John R. Krouse
Publisher:
ISBN:
Category :
Languages : en
Pages : 42
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Wind-tunnel tests were conducted at a Mach number of 6.26 to determine the longitudinal aerodynamic characteristics of several conceptual hypersonic aircraft configurations, consisting of various half-cone-cylinder bodies and double-delta wings. Effects of body volume, vehicle orientation, wing planform, and wing-tip dihedral were determined. In general, the lift-to-drag ratios of all high-wing configurations varied slightly over an angle-of-attack range of 0 degrees to 12 degrees reaching maximum values of roughly 3.2 near 6 degrees. On the other hand, the lift-to-drag ratios of all low-wing configurations increased continuously with increasing angle of attack, eventually reaching maximum values of roughly 3.6 near 10 degrees. In all cases, fuselage base drag accounted for less than 10 percent of the total drag. For the arbitrarily chosen center-of-gravity location, all low-wing configurations were stable but unbalanced; whereas several high-wing configurations were both stable and balanced. (Author).
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 32
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