Some Pressure-distribution Measurements on a Swept Wing at Transonic Speeds by the NACA Wing-flow Method PDF Download
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Author: J. Ford Johnston
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Category :
Languages : en
Pages : 19
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Author: J. Ford Johnston
Publisher:
ISBN:
Category :
Languages : en
Pages : 19
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Author: Edward C. B. Danforth
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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: United States. National Advisory Committee for Aeronautics
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ISBN:
Category : Aeronautics
Languages : en
Pages : 580
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Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 750
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Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 508
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Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 1368
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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: Kenneth W. McAlister
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ISBN:
Category : Aerodynamic load
Languages : en
Pages : 150
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Author: United States. National Aeronautics and Space Administration
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Category :
Languages : en
Pages :
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Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages :
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Book Description
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
