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

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CAE CalculationsModes File Mapping File Aerodynamic GridStructural ModelStructural NodesElement ConnectivitySurface GridÌÔÖÓ××ÓÖ×ØÖÙØÙÖÐÐ××¬ØÓÒ×ØÓÐÐÓÛÒ×ØÔ× ÙÖ¿º¾ÓÑÔÓÒÒØ×ÓÒÖÓÐ×ØÐÙÐØÓÒ×Multilevel Mapping¯ÌÜØÖØÖÔÓÒØ×ÖØÒØÖÒÙÐØÙ×ÒÐÙÒÝØÖÒÙÐØÓÒºÌ ¯Ì×ØÖÙØÙÖÐÒÓ×ÓÖÓÑÔÓÒÒØÖÜØÖØÖÓÑØÅÑÓÐÐÒØÓÓÐº ÓÙØÔÙØÖÓÑØ××ÓÒÒØÚØÝØÒ¬ÐÛØÐÑÒØÓÒ××ØÒÓØÐÒ ÒÙÑÖ×ÓØ¿ÒÓ×ÖÓÑØÒÓÐ¬ÐºÓÑÔÓÒÒØÐÐ×ÚÒØÓØÖÒÙÐÖ¯ÌÒÓÐ¬Ð×ÒØÓÖÖ×ÔÓÒÒÐÐÐÐÑÒØÓÒÒØÚØÝ¬Ð×Ö××ÑÐ ÐÑÒØ¸ÒØÙÖÖÒØ×¸½ÓÖÙ×ÐÐÑÒØ×¸¼ÓÖÛÒ¸¾ÓÖÔÝÐÓÒÒØ¿ÓÖÒØÓ×ÒÐÒÓ¬ÐÒ×ÒÐÓÒÒØÚØÝ¬Ðº ØÒÐÐºÖÓØÚÖÓÙ×ÓÑÔÓÒÒØ×ÖÐ×ÓÐÐÐºÀÓÛÚÖØÐÐÐÒ×ÓÒÙÖÒØÖ ÒÖØÓÒ×ØÔØ×ÐºÌÒÓ×ÓÒØÙ×ÐÓØÖÓÝÒÑÖÖÐÐÐ×¼¼¼½¸ ÄØÐÑÒØ×ÓØ×ØÖÙØÙÖÐÓÑÔÓÒÒØ×ØÒÓ×ÐÝÒÓÒØ×ÙÖÓØÖÓÝÒÑ¬ÐÓÒØÒ×ØÒÓÐÓÓÖÒØ×ÐÓÒÛØØÐÐ×ºÌÐÒÒÓØÐÑÒØ×ÓØ ÓÒØÛÒ¼¼¼¼¸ÓÒØÔÝÐÓÒ¼¼¼¾ÒÓÒØÒÐÐ¼¼¼¿ºÒÖÓÝÒÑ×ÙÖÖ ×ØÖÙØÙÖÐÓÑÔÓÒÒØ×ØÓØÒÓ×ÓØÓÖÖ×ÔÓÒÒÓÑÔÓÒÒØ×ÓÒØÖÓÝÒÑÖ ×ÓÒÒ×ÑÐÐ¬ÐºÌ×¬ÐÐ××¬×ØÓÑÔÓÒÒØ×ÒØÓØÖÖ×ÔØÚÖÖ×ºÓÖ ½¼¼¼½½ ØÙÖÖÒØ×ØÐÒÒ××ÓÐÐÓÛ×¼¼¼¼¼¾ ¾¼¼¼¾¿¿¼¼¼¿¾ ¿
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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 and 56: Flap´µFlapWingBlended width of th
Page 57 and 58: WingFlapFlap´µWingGapSheared cell
Page 59: Case 3: Mach 0.769, frequency 5 Hz.
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Page 65 and 66: ÙÖº½ÌÌÛÒØÙÒÒÐÑÓÐÛ
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Page 69 and 70: WingDeflected flapØØØÖÙÖÕÙ
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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
Page 107 and 108: 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
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Generalised coordinate (rudder mode
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Aeroelastic Analysis of Aircraft with Control Surfaces ... - CFD4Aircraft

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