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23:, static or dynamic, in such a fashion as to affect the aerodynamic and structural performance of that aircraft in a beneficial way", or "passive aeroelastic control". Objectives associated with aeroelastic tailoring include weight minimization, flutter, divergence, stress, roll reversal, control effectiveness, lift, drag, skin buckling, and fatigue.
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According to Shirk et al., the first record of aeroelastic tailoring is from 1949 by Munk, who oriented the grain of his wooden propeller blade to create desirable deformation couplings when operated. In the late 1960s, there was a thrust in aeroelastic tailoring research, which has continued fairly
52:. Enhanced fabrication processes for composite laminates offer new design possibilities that have not been fully exploited for optimal aeroelastic performance and weight savings.
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are two aeroelastic tailoring examples highlighted by
Weisshaar. Today the use of composite materials is becoming more prevalent in transport aircraft, including the
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Munk, M., "Propeller
Containing Diagonally Disposed Fibrous Material," U.S. Patent 2,484,308,1111, Oct. 1949.
106:"Aeroelastic Tailoring of Transport Aircraft Wings: State-of-the-Art and Potential Enabling Technologies"
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is defined as "the embodiment of directional stiffness into an aircraft structural design to control
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Shirk, M., Hertz, T., Weisshaar, T., "Aeroelastic
Tailoring – Theory, Practice, Promise",
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This article incorporates text from this source, which is in the
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steadily through to today. The forward swept wings of the
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Jutte, Christine; Stanford, Bret K. (1 April 2014).
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