Aeroelastic Analysis of Aircraft with Control Surfaces ... - CFD4Aircraft

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B-F-R Case, Euler Simulation, Mach 1.05´µÌ¹¹Ê×ØÅ½º¼P: 0.420 0.477 0.522 0.567 0.612 0.659 0.704 0.750 0.797 0.841 0.890B-F-R-T Case, Euler Simulations, Mach 1.05´µÌ¹¹Ê¹Ì×ØÅ½º¼P: 0.4330 0.5041 0.5600 0.6158 0.6700 0.7275 0.7800 0.8392 0.8900B-F-W-R-T Case, Euler Simulation, Mach 1.05ÙÖº¿¿ÀÛ×ØÝÔÖ××ÙÖÓÒØÓÙÖ×ØÅ½º¼ÓÖÒÖ×ÒÐÚÐÓÓÑØÖ ÓÑÔÐÜØÝ×ÓÛÒØÖÙÐÓÖÑØÓÒÓ×ÓÓØ¬Òº××´µÒ´µÛØÓÙØ ´µÌ¹¹Ï¹Ê¹Ì×ØÅ½º¼P: 0.433 0.484 0.524 0.565 0.606 0.646 0.687 0.728 0.768 0.809 0.849 0.890ØÛÒ×ÓÛ×ÓÓÚÖØÖÙÖº ½¿
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Structural ComponentLevel 1 Mapping
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Control surface treatmentsBlended e
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Flap´µFlapWingBlended width of th
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WingFlapFlap´µWingGapSheared cell
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Case 3: Mach 0.769, frequency 5 Hz.
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Rigid fuselageHierarchy level 1Wing
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Case 3: Mach 0.769, frequency 5 Hz.
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Generalised coordinate (wing bendin
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Magnitude of unsteady pressure (non
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P: 0.6 0.666667 0.733333 0.8 0.8666
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Magnitude of unsteady pressure (non
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Page 97 and 98: 0.020.02Generalised Coordinate0.010
Page 99 and 100: 10.90.00250.8Generalised Coordinate
Page 101 and 102: 4040Initial grid velocity 0.02Initi
Page 103 and 104: Unsteady force on the flap0.00100.0
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Page 107 and 108: 20152010Flap angle [degrees]50-5-10
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Page 143: -Cp on the fin at Y=2.4 MetresBAE-F
Page 147 and 148: CFDLinearB-F-R (Onset of buzz)B-F-R
Page 149 and 150: Generalised coordinate (rudder mode
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Aeroelastic Analysis of Aircraft with Control Surfaces ... - CFD4Aircraft

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