The Subsonic Static Aerodynamic Characteristics of an Airplane Model Having a Triangular Wing of Aspect Ratio 3 PDF Download
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Author: Howard F. Savage
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 662
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Book Description
An investigation has been conducted to determine the effects of vertical-tail location and size on the subsonic aerodynamic characteristics of a model having a triangular wing. The wing had an aspect ratio of 3, an NACA 0003.5-63 section in the streamwise direction, and plain, trailing-edge ailerons. The wing was attached to the fuselage in either a mid or high position and an unswept horizontal tail was located on the fuselage center line. Two vertical tails were tested which had areas of 26.7 or 20.3 percent of the wing area. Each vertical tail was equipped with a rudder and had a geometric aspect ratio of 1.5, a taper ratio of 0.16, and 54 degrees of sweepback of the leading edge. Each vertical tail was tested at two different tail lengths. The wind-tunnel tests were conducted at a Reynolds number of 2.5 milMon at Mach numbers from 0.25 to 0.95.
Author: Howard F. Savage
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 662
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Book Description
An investigation has been conducted to determine the effects of vertical-tail location and size on the subsonic aerodynamic characteristics of a model having a triangular wing. The wing had an aspect ratio of 3, an NACA 0003.5-63 section in the streamwise direction, and plain, trailing-edge ailerons. The wing was attached to the fuselage in either a mid or high position and an unswept horizontal tail was located on the fuselage center line. Two vertical tails were tested which had areas of 26.7 or 20.3 percent of the wing area. Each vertical tail was equipped with a rudder and had a geometric aspect ratio of 1.5, a taper ratio of 0.16, and 54 degrees of sweepback of the leading edge. Each vertical tail was tested at two different tail lengths. The wind-tunnel tests were conducted at a Reynolds number of 2.5 milMon at Mach numbers from 0.25 to 0.95.
Author: Bruce E. Tinling
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 37
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Book Description
A wind-tunnel investigation has been conducted to determine the low-speed aerodynanmic characteristics of an airplane arrangement having an unswept horizontal tail and a triangular wing of aspect ratio 3 equipped with partial-span single-slotted flaps and plain ailerons. The effects of flap deflection on the longitudinal characteristics were investigated for tail positions either in or 10 percent of the wing semispan below the wing-chord plane. The rolling moment produced by the ailerons when the flaps were deflected was measured as well as the rolling moment produced by differential deflection of the horizontal-tail surfaces. The effects of small positive flap deflections on the longitudinal characteristics at Mach numbers up to 0.95 were also investigated. Most of the data were obtained at a Reynolds number of 2,500,000.
Author: Bruce E. Tinling
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 85
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Book Description
An investigation has been conducted to determine the effects of horizontal-tail location and size on the longitudinal aerodynamic characteristics of an airplane model having a triangular wing. The wing had an aspect ratio of 3 and the NACA 0003.5-63 section in the streamwise direction. Two horizontal tails were tested which had areas of either 16.7 or 21.9 percent of the wing area. Each of the horizontal tails had an aspect ratio of 4, a taper ratio of 0.33, the NACA 0004-64 section, and no sweepback of the 50-percent-chord line. Tests were conducted with the horizontal.tails located -0.10, 0, 0.10, and 0.20 wing semispans above the chord plane of the wing at longitudinal distances of 1.2 and 1.5 mean aerodynamic chord lengths behind the moment center. The wind-tunnel tests were conducted at a Reynolds number of 2.5 miJJion at Mach numbers from 0.25 to 0.95.
Author: Howard F. Savage
Publisher:
ISBN:
Category :
Languages : en
Pages : 82
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 388
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 818
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Author:
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 100
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Author: Robert H. Neely
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 96
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Book Description
Author: Louis A. Girifalco
Publisher:
ISBN:
Category : Crystals
Languages : en
Pages : 1082
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Book Description
A general theory of solid-state diffusion in strained systems is developed on a molecular-kinetic basis. The theory predicts that for simple strains the diffusion coefficient is an exponential function of the lattice parameter and that the rate of change of the diffusion coefficient with strain is linearly related to the interatomic forces. It has also been shown that for plastic flow the diffusion coefficient is a linear function of strain rate. All the conclusions are confirmed by the data available in the literature.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 940
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Book Description
