Pressure-distribution Measurements Over a 45 Degree Sweptback Wing at Transonic Speeds by the NACA Wing-flow Method PDF Download
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Author: Edward C. B. Danforth
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 42
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Book Description
Measurements of pressure were made over the chord of a swept-wing model at four stations along (2, 6, 50, and 82 percent semispan) by the NACA wing-flow method. The model tested was an untapered 45 degree sweptback wing of aspect ratio 3.5 with 2-inch-chord NACA 65-210 airfoil sections normal to the leading edge. The tests were conducted at Mach numbers from about 0.7 to 1.1 at angles of attack from -1 to 4 degrees. The Reynolds number of the tests was nominally 600,000 based on the wing chord in the stream direction. The results are presented to show the chordwise pressure distributions and the spanwise distributions of section lift, drag, and pitching moment.
Author: Edward C. B. Danforth
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 42
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Book Description
Measurements of pressure were made over the chord of a swept-wing model at four stations along (2, 6, 50, and 82 percent semispan) by the NACA wing-flow method. The model tested was an untapered 45 degree sweptback wing of aspect ratio 3.5 with 2-inch-chord NACA 65-210 airfoil sections normal to the leading edge. The tests were conducted at Mach numbers from about 0.7 to 1.1 at angles of attack from -1 to 4 degrees. The Reynolds number of the tests was nominally 600,000 based on the wing chord in the stream direction. The results are presented to show the chordwise pressure distributions and the spanwise distributions of section lift, drag, and pitching moment.
Author: J. Ford Johnston
Publisher:
ISBN:
Category :
Languages : en
Pages : 19
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Author: Jack F. Runckel
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 104
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Book Description
An investigation at transonic speeds of the loading over a 45 degree sweptback wing having an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections has been conducted in the Langley16-foot transonic tunnel. Pressure measurements on the wing-body combination were obtained at angles of attack from 0 to 26 degrees at Mach numbers from 0.80 to 0.98 and from 0 to about 12 degrees at Mach numbers from 1.00 to 1.05. Reynolds number, based on the wing mean aerodynamic chord, varied from 7,000,000 to 8,500,000 over the test Mach number range.
Author: Jack F. Runckel
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 98
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Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 568
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Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 580
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Author: Kenneth W. McAlister
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 150
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Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages :
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Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1056
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Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category :
Languages : en
Pages : 208
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