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

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Model 1-Flap oscillating mode 16.2 HzModel 1-First wing bending mode 10.39 HzModel 2-First wing bending mode 10.44 HzRigid fuselage gridRigid wingRigid wingÙÖº½ËØÖÙØÙÖÐÑÓÐ×ÛØØÔÓ×ÐÐØÓÒÑÓÒØ¬Ö×ØÛÒÒÒÑÓ ´µÐÔÑÓ ´µÅÓÐ½ ´µÅÓÐ¾Oscillating flapDeformed in first modeDeformed in first modeÖÐÙ×ØÖÖÓÙÒØØÖÐÒÒØÔÖÓÒÛÖØ×Ó×ÐÐÝØÓÚÐÓÔ ÙÖº¾¿¹ÐÓ×ØÖØÝØÓÔÖÚÒØÓÐÐÔ×ÔÓÒØØØÐÒÓØÛÒÖÓÓØÒØ×ÔÒ¹Û×ÖØÓÒÓÒØÔºÌ×ÞÓØÚ×ÓÙ×Ö×¼¼ÐÐ×ºÌÖ× ÒÑÓÚÙÖÒØÙÞÞ×ÑÙÐØÓÒºÌÖÖ½ÐÐ×ÒØÓÖ¹Û×ÖØÓÒÒ¾Ø×ÑØÓÔÓÐÓÝ×ØÚ×ÓÙ×ÖºÌ¬ÒÙÐÖÖ×½ºÑÐÐÓÒÐÐ×ºÌÖÖ¾ ÔÐÓÙÖØÐÝÖ×ÓÐÚÒØÓÛÒØÖÓÒÓÒØÖ×ØÙØØØ×ÑØÑ××ÑÐÐ ÒÓÙØÓÐÐÓÛÖÔØÙÖÒÖÓÙÒÓÖØÙÒ×ØÝÐÙÐØÓÒ×ºÌÐÒÙÐÖÖ×ÚÓÖ×Ö×ÓØÒÖÓÑØ¬ÒÖÝÖÑÓÚÒÚÖÝÐØÖÒØÖÔÓÒØÒÐÐØ ØÖÖØÓÒ×ºÌÓÖ×ÙÐÖÖ×¾¼¼ÐÐ×ºÌÖÙ×ÓÖÔ×ÛØÔ××Ø ÐÐ×ÒØÓÖ¹Û×ÖØÓÒÒ¼×ÔÒ¹Û×ºÌÛÐÐ×ÔÒ×½¢½¼ ¿ÓÖÐÒØ×ºØÔ×ÒØÛÒº ×Ñ×ØÓÖ×ÙÐÖÖÓÖÐÒÔ×ÙØÛØØÛÓÜØÖÐÓ×Ò×Ô×ØÛÒ¿
3020∆ t = 0.1∆ t = 0.05∆ t = 0.0254030Fine grid ∆t = 0.1Fine grid ∆t = 0.05Coarse grid ∆t = 0.05Flap angle [degrees]1000-10´µÊÆËÐÙÐØÓÒ¸Å¼º¸¼ºÒ-10ÝÒÑÔÖ××ÙÖ¾ºÈ-20-20-30ÙÖº¿ÌÑ×ØÔÒÖÖ¬ÒÑÒØÐÙÐØÓÒ× ÒÑÔÖ××ÙÖ¾ºÈ ´µÙÐÖÐÙÐØÓÒ¸Å¼º¸¼ºÒÝ¹-300 10 20 30 400 10 20 30 40 50 60Nondimensionalised timeNondimensionalised timeÌ×ØÝÒÙÒ×ØÝÖ×ÙÐØ×ÓÖ×ÛØÓÖÔÑÓØÓÒÚÒÚÐØÛØ º¾ ØÜÔÖÑÒØ×ÒÔØÖºÌÙÖÖÒØÔØÖÐ×ÛØÔØØ×ÖÚÒÝØ Ê×ÙÐØ×Ò×Ù××ÓÒ×ÚÐØÓÒº ÙÒ×ØÝÖÓÝÒÑ×ÒÙÒÐØÔÖÚÓÙ××ÜÔÖÑÒØÐÖ×ÙÐØ×ÖÒÓØÚÐÐÓÖØÑ×ØÔÖ¬ÒÑÒØ×ØÙÝÛ×ÔÖÓÖÑÓÒØÊÆË×ØÅ¼ººØÖ×ØÖÑ º¾º½ÖÒØÑ¹×ØÔÖ¬ÒÑÒØ×ØÙÝÙÖÚ×ÓØÑ×ØÔ×¼º¼¾Ò¼º¼ÐÑÓ×ØÓÚÖÐÔÓØÖÒÑÒØÒØÖÕÙÒÝÒ ØÑØÖ×ÓØÑÓÐÖ×ÔÓÒ×Ù×ÒØÑ×ØÔ×Ó¼º¼¾¸¼º¼Ò¼º½º×Ò×ÒØ ÚÐÓØÝÓ¾Ñ×ØÖÙÖÕÙÒÝÓØÖ×ÔÓÒ××¼ººÙÖº¿´µ×ÓÛ×ØÙÖº¿´µ×ÓÛ×ØÑÓÐÖ×ÔÓÒ×ØÅ¼ºÙ×ÒØÙÐÖÐÙÐØÓÒ×ÓÒ¬ÒÒ ÓÖ×Ö×ÛØØÑ×ØÔ×Ó¼º¼Ò¼º½ºÇÒÒØÑÓÐÖ×ÔÓÒ×ÙÖÚ×ÓÚÖÐÔ ØÑÔÐØÙºÀÒØÑ×ØÔÓ¼º¼×Ù×ÓÖÐÐØÙÞÞ×ÑÙÐØÓÒ×ÒØÙÖÖÒØ×ØÙÝºÔÖØØÔÖ×ÔÓÒ×º ÓØÖºÌÖ×ÙÐØ×ÒØØÓÖ×ÙÐÖÖÛØØÑ×ØÔÓ¼º¼ÖÐØÓÕÙØÐÝÌ××ØÓÒÓÒÖÒ×Ø«ØÓØÐÒÒÔÖÑØÖ½℄ÓÒØÓÒ×ØÓÙÞÞºÒ º¾º¾ÔÒÒÓÙÞÞÓÒÔÐÒÒ ÓÖ×ÙÐÖÖ×Ù×ØÓ××××Ø×«Ø×ÛÖÓÒÖÒÛØØÚÖØÓÒÒØØÐÒÒÔÖÑØÖØÑÓÖØØÖÒ×ÓÖÑÙÖÓÒÓÖÑ×ØÓØ×ØÖÙØÙÖÐÖØ ÔÖØÙÞÞÅÒÙÑÖÛØÒÒØÐÒÒÔÖÑØÖºÁÒØ¬Ö×Ø×ÐÓÛ ÐÒÒÚÐÙÓ¾¼ÒÒØ×ÓÒÖÚÐÙÓ½¼¼×Ù×ºÌÐÖÖØÚÐÙÓ Flap angle [degrees]2010
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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 and 60: Case 3: Mach 0.769, frequency 5 Hz.
Page 61 and 62: Rigid fuselageHierarchy level 1Wing
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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
Page 87 and 88: ÓÒØÖÓÐËÙÖÁÒ×ØÐØÝ Ô
Page 89: ÅÓ ÏÒÒÒ ÐÔÇ×ÐÐØÓÒ ½
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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Page 133 and 134: 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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