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: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 940
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 522
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Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1516
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Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 716
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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: P. W. Kuhns
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 736
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Equations are derived to evaluate the effects of thermal vibration relaxation and specific-heat changes on pneumatic-probe pyrometer measurements in the region 1000 to 3000 degrees K and 0.3
Author: Defense Documentation Center (U.S.)
Publisher:
ISBN:
Category : Industrial arts
Languages : en
Pages : 922
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Author:
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 100
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