Longitudinal Aerodynamic Characteristics of a High-subsonic-speed Transport Airplane Model with a Cambered 40° Sweptback Wing of Aspect Ratio 8 at Mach Numbers to 0.96 PDF Download
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Author: Atwood R. Heath
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 92
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Book Description
Author: Atwood R. Heath
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 92
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 96
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Book Description
Author: Atwood R. Heath
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 88
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Book Description
Author: James H. Parks
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 42
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Book Description
Author: Paul G. Fournier
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 72
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Book Description
Author: Gerald Hieser
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 64
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Book Description
Author: Edward J. Ray
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 84
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Book Description
Author: Eugene N. Brooks
Publisher:
ISBN:
Category :
Languages : en
Pages : 44
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Book Description
Author: Odell A. Morris
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 72
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Book Description
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.
