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

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Fluid Grid Node−1,1η1,1(x,y)(ξ,
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X1s,kPurely translated fictitious p
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Structural ComponentLevel 1 Mapping
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Control surface treatmentsBlended e
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¿ººÔÐÓ× ÒÓØÖÓÔØÓÒÓ
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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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3020∆ t = 0.1∆ t = 0.05∆ t =
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0.020.020.0150.015Generalised Coord
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0.020.02Generalised Coordinate0.010
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10.90.00250.8Generalised Coordinate
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4040Initial grid velocity 0.02Initi
Page 103 and 104: Unsteady force on the flap0.00100.0
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Page 141 and 142: Spanwise locations on the fin of th
Page 143 and 144: -Cp on the fin at Y=2.4 MetresBAE-F
Page 145 and 146: B-F-R Case, Euler Simulation, Mach
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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