NASA Technical Note PDF Download
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Author:
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Category :
Languages : en
Pages : 780
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Book Description
Author:
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ISBN:
Category :
Languages : en
Pages : 780
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Author: James W. Wiggins
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ISBN:
Category : Airplanes
Languages : en
Pages : 56
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Book Description
An investigation was performed in the Langley high-speed 7- by 10-foot tunnel in order to determine the rolling derivatives for swept-wing-body configurations at angles of attack from 0 degrees to 13 degrees and at high subsonic Mach numbers. The wings had sweep angles of 3.6 degrees, 32.6 degrees, 45 degrees, and 60 degrees at the quarter-chord line, an aspect ratio of 4, a taper ratio of 0.6, and an NACA 65A006 airfoil section parallel to the free stream. The results indicate a reduction in the damping-in-roll derivative at the higher test angles of attack. Of the wings tested, instability of the damping-in-roll derivative was experienced over the largest ranges of angle of attack and Mach number for the 32.6 sweptback wing.
Author: United States. National Advisory Committee for Aeronautics
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Category : Aeronautics
Languages : en
Pages : 388
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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 : 442
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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 : Mechanics, Applied
Languages : en
Pages : 742
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Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1076
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Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 584
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Author: James T. Matthews
Publisher:
ISBN:
Category : Acceleration (Mechanics)
Languages : en
Pages : 726
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Book Description
A theoretical analysis was made to investigate the performance and acceleration-restriction capabilities of a normal-acceleration command control system in a fighter airplane. Several combinations of pitching velocity and pitching acceleration were investigated as feedback quantities in combination with normal acceleration.
