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

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UndeflectedHigher heirarchycomponentLower heirarchycomponentTransformedStructural gridBlended transformedÙÖ¿º½«ØÓÐÒÒÓÒØÛÓÓÑÔÓÒÒØ×Ý×ØÑ0.20.18Effect of blending on the modal responseblending of -10dblending of -30dGeneralised velocity0.160.140.120.10.080.060.04Å¼º¿º ÙÖ¿º½«ÖÒÒØÑÓÐÖ×ÔÓÒ×ÛÒÙ×ÒØÛÓ«ÖÒØÐÒÒÔÖÑØÖ×Ø0.020-0.020 10 20 30 40 50 60 70T*
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Page 37 and 38: ¿º¿ ×Ù×ØÓØÖÒ×ÖÓÖ×º
Page 39 and 40: Fluid Grid Node−1,1η1,1(x,y)(ξ,
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Page 45 and 46: BBPÙÖ¿ºËÖ××ÛÒÔÐÒÔÖÓ
Page 47 and 48: X1s,kPurely translated fictitious p
Page 49 and 50: Structural ComponentLevel 1 Mapping
Page 51 and 52: Control surface treatmentsBlended e
Page 53 and 54: ¿ººÔÐÓ× ÒÓØÖÓÔØÓÒÓ
Page 55: Flap´µFlapWingBlended width of th
Page 59 and 60: Case 3: Mach 0.769, frequency 5 Hz.
Page 61 and 62: Rigid fuselageHierarchy level 1Wing
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Page 65 and 66: ÙÖº½ÌÌÛÒØÙÒÒÐÑÓÐÛ
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Page 73 and 74: ÑÓÖ×¾ØØÖ×ÓÒÒØÖÕÙÒ
Page 75 and 76: ´µËØÖÙØÙÖÐÑÓÐY:´µÅ
Page 77 and 78: Case 3: Mach 0.769, frequency 5 Hz.
Page 79 and 80: Generalised coordinate (wing bendin
Page 81 and 82: Magnitude of unsteady pressure (non
Page 83 and 84: P: 0.6 0.666667 0.733333 0.8 0.8666
Page 85 and 86: Magnitude of unsteady pressure (non
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Page 91 and 92: 3020∆ t = 0.1∆ t = 0.05∆ t =
Page 93 and 94: 15Flap with gapsBlended flap30Flap
Page 95 and 96: 0.020.020.0150.015Generalised Coord
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
Page 105 and 106: Unsteady force on the flap (nondime
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20152010Flap angle [degrees]50-5-10
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CFDNastranDynamic pressureBuzz regi
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The Hawk Body-Fin-Wing-Rudder CaseO
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Spanwise locations on the fin of th
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-Cp on the fin at Y=2.4 MetresBAE-F
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B-F-R Case, Euler Simulation, Mach
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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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