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

More documents

Recommendations

Info

ÒÓØÖÛ×ÑÓ×ØÛØ×ÚÒØÓØÐÚÐØÛÓÓÑÔÓÒÒØÖÚÒØÖÒ×ÓÖÑØÓÒºÌÖÕÙÖºÌ«ØÓØ×ÔÖÑØÖÓÒÖÓÐ×Ø×ØÐØÝ×ÑÚÒØÒÔØÖ¿º ÜÔÓÒÒØÐÙÒØÓÒ ÓÖÑÓ×ØØ×Ø××ÙØ×ÓÑÜÔÖÑÒØØÓÒÛØÙÒØÓÒ×ÒÔÖÑØÖ×ÓÖÓØÖ××ÑÝ ½¼ÓÒØÒ×ØÐÒÒÔÖÑØÖ ½¼Ò×ÓÙÒØÓ×ÙØÐÓÖÅÓÖÓÚÖØ×ÔÖÑØÖ×Ð×ÓÙ×ØÓØ×ÑÓÓØÐÒÒØÓÒØÖÓÐ×ÙÖÒÓÖÒ ÓÙØÓÖ×º ØÒÛÑÙÐØ¹ÐÚÐ×Ñ×Ð×Ó×ÑÐÐºÇÒÓ×ØÖÓÙÒ×ØÖ×ÒÓØÓÒØÓÙ×ÒØ ÜÔÓÒÒØÐÙÒØÓÒÒØÛØÒÙØØÛØ×ÖÐÙÐØ×ÔÖØÓÔÖÔÖÓ××Ò ÌÓ×ØÓÓÑÔÙØÒØÓÖÒÐÎÌØÖÒ×ÓÖÑØÓÒ××ÑÐÐÒØÓ×ØÓÔÔÐÝÒ×ØÔ×ÓØ××Ò×Ò¬ÒØºÐÒºÌÒÓÖÒÓÙØÓÖ×ÓØÓÒØÖÓÐ×ÙÖ×ÖÖÒÒÓØÐÒ ¿º ÌÛÒØÖÐÒÓÒØÖÓÐ×ÙÖ×ÖÙ×ÙÐÐÝÑÓÐÐ×ØÖÙØÙÖÐÐÝ×ÔÐØ×ÒØØ× ÓÒØÖÓÐËÙÖÌÖÒ×ÓÖÑØÓÒÒØÓØÛÒºÓÑÔÙØØÓÒÐ×ÑÙÐØÓÒ×ÒÚÓÐÚÒÑÓÚÒÓÒØÖÓÐ×ÙÖ×Ö×ØÐÐÒÓØÓÑÑÓÒØÖØÛØÒØÖÑÛÓÖÓÑÙÐØÐÓÓºÌÖÖÒÙÑÖÓÛÝ×¿ÔÒ ×ÓØÔÙ×ÓÑØÖÐ×ÓÒØÒÙØÝÐÓÒØÛÒ×ÔÒÛ×ÆÙÐØØÓ ÑÒÐÝÙØÓØÆÙÐØÝÒØÖØÒØÖÓÚÖÒÖÓÙÒØÓÒØÖÓÐ×ÙÖ×ºÌÖ×Ù×ÕÙÒØ×ØÓÒ×º ÑÓÐÐÒÑÙÐØÐÓÒÚÖÓÒÑÒØ×Ð×ØÒÙÖ¿º½¿ÒÖÖÝ×ÖÒØ¿ºº½ÌÖÒ×ÔÖØÓÒ ÓÖÒØÓÓÛØÔ×ÖÑÓÐÐØÔØÖØÑÒØÒÖÓÐÝÐ××¬ÒØÓ ØÛÓØÓÖ×¸ÐÒÒÔÛØÖ×ºÌÐÒØÖØÑÒØ×ÖÑÓÖÓÑÑÓÒ ÙØÓ×ÑÔÐØÝÒ×ÓÑÔÐÑÒØØÓÒº ×ØÓ×ÒÓØÖÕÙÖÓÖÑØÓÒÓØÚÓÐÙÑÖºÌ×ÑØÓ×ÑÒ×ØÓÑÒÓÙÚÖ ØÓÛ×ÓÐÚÖÒØÓ×ÒØÓÒÓØ×ÙÖÛÒÒØØÖ×ÒÓÒ¿℄ºÌ× ÇØÐÒØÖØÑÒØ×ØÖÒ×ÔÖØÓÒ×ÓÒÓØÓÐ×ØÑØÓ×Ò××ÝØÓÑÔÐÑÒØÒÓÛÒ¸ÖÓÑÅ×ÓÐÚÖÓÖÜÑÔÐ¸ØÒØ×ÒÖØÐÝÔÔÐØÓØÖ× ××ÖÒ¿¸℄××ÙÑÑÖ×ÖºÁØÚÖØÓÒÒØ×ÙÖÒÓÖÑÐ×××ÙÖ×ÖÓÙØÓÙØÝÒÒØÚÐÓØÝÓÙÒÖÝÓÒØÓÒ×ÓØ«ØÒÓ×º ÌÒÒÓÙÒÖÝÓÒØÓÒÓÑ×ÒÓÖÑÓØÓÒÐÙÚÐÓØÝÓÙØ×ÓØ ØÖÓÙÑÓ¬ØÓÒÓØÜ×ØÒ×ÙÖÒÓÖÑÐ×ºÒÒØÓÖÒØØÓÒÓØÜ×ØÒ×ÙÖÐÑÒØ×ºÌ×ØÓÒÐÚÐÓØÝ«Ø×ØÛÝØÙÒ×ØÝÓÛ×ÓÐÚÖ Ö×ÓÐÚ×ØÓÛØÒÒÝÓÙÒÖÝÓÒØÓÒ×××ÓÛÒÒÙÖ¿º½ºÀÖØÎÇÖÒÐ× ØÓÖÒÐØÒÒØÐÚÐÓØÝÛØÒÓÖÑÐÒºÁÒÑÓÚÒÓÒØÖÓÐ×ÙÖØ××ÙÖÒÓÖÑÐ Ò×ØÓÒÛÚÐÙÒÆÛºÁÒ×ØÝØÓÛØÒÒÝÓÙÒÖÝÓÒØÓÒ×ÜÔÖ×××Ø×ÓÒØÓÒ×ÑÔÐÝ×ØØ×ØØØÚÐÓØÝÒÓÖÑÐØÓØÓÝÑÙ×ØÞÖÓºÓÖØÝÒÑ ÎÒ¼ ´¿ºµ¿
<strong>Control</strong> surface treatmentsBlended edgesFree edgesTranspirationChimera gridsÙÖ¿º½¿«ÖÒØØÝÔ×ÓÓÒØÖÓÐ×ÙÖØÖØÑÒØÒÒÐÝ××ºRigid blendingSliding planesMultilevel blending (current work)Virtual zoneGap blocks (current work)^nNewVTranspirationV New^nOriginal×ØÕÙØÓÒÓÖÓÛØÒÒÝÓÒØÓÒ×ÜÔÖ××× ÙÖ¿º½ÔÔÐØÓÒÓØØÖÒ×ÔÖØÓÒÚÐÓØÝVOriginalÒÑÒ×ØØØÚÐÓØÝÒÓÖÑÐØÓØ×ÙÖÙ×ØÕÙÐØÓØÚÐÓØÝÓÓÝÒÓÖÑÐ ØÓØ×ÐºÀÒØÒ×ÙÖ×ØØÒÓÓÛÒÔ××ØÖÓÙØ×ÙÖºÁØ×ÓÙÐÒÓØØØ ÎÒÎÒ ´¿ºµÎ×ÒÓØÕÙÐØÓÎÌÖÒ×ÔÖØÓÒÐÒÙÖ¿º½º ¿ºº¾ÊÐÒÒÓÑØÖÝÙØÓÖÑÓ×Ø××ÛØ×ÑÐÐÑÔÐØÙÖÓØØÓÒ×ÓØÔØ×ÑØÓ×Ö×ÓÒÐÝ ØÛÒ×ÙÖºÌÐÒÒÓ×Ù×ÚØÓÒÖÓÑØÔÖÓÔÖÖÔÖ×ÒØØÓÒÓØÔ ÇÒÓØ×ÑÔÐ×ØØÒÕÙ××ØÐÒÒÓÒÓÖÒÓÙØÓÖ×ÓØÔÛØÙÖØºÝÖÐÒÒØ×ÑÒØØØØÖ×ÒÓÓÒØÖÓÐÓÒØÐÒØÓØÐÒ ÖÓÒºÌÐÒÖÓÒÒÐÙ×ØÐÐ×ÓØÔ×ÛØÓÖÑ×ØÔ ×ÑÙÐØÓÒ×ºº ÑÓÚ×ºÊÔÐÒÒ×ÒÙ×ÓÖÓØÓÖÔÒÖÓÝÒÑÐÐÝÖÚÒÔ
Page 1 and 2: ÖÓÐ×ØÒÐÝ××ÓÖÖØ ÛØÓ
Page 3 and 4: ×ØÖØÒØ×Ò×ØºÍÒØÐØÚ
Page 5 and 6: ÓÒØÒØ×½ÁÒØÖÓÙØÓÒ ½
Page 7 and 8: º¿ÄÑØØÓÒÓÄÒÖÖÓÝÒÑ
Page 9 and 10: ÔÔÐÖÓÝÒÑÓÖ×ºÌÖÓÝÒ
Page 11 and 12: ÒÚÓÐÚØÖÒ×ÓÒÓÒØÖÓÐ
Page 13 and 14: ÌÑÓØÚØÓÒÓÖØÙÖÖÒØÛ
Page 15 and 16: ÓØÒ×ØÐØÝÓÙÒÖÝØØÖÒ
Page 17 and 18: ¾º¾º½ÆÓÒ¹ÑÒ×ÓÒÐÓÖ
Page 19 and 20: ÒÐÐÝ¸ØÐÑÒÖÚ×Ó×ØÝ×
Page 21 and 22: ÛÖ½Â ÏÏÂ ½Â Ü·Ý·ÞÀ¡
Page 23 and 24: ÇÒØÓØÖÒ¸ØÖØÚØÒÕÙ×
Page 25 and 26: AB×ÖÓÙØÓÙØÒ×ØÔ½ºÒÐ
Page 27 and 28: Ì×ÖÐÙÐØ× ÛÖ×½´µ×¾´
Page 29 and 30: ÒÖÐÙÐØÖÓÑ ÌÙÒØÓÒ×Ò
Page 31 and 32: Å××ÒÖÐ×ØÓÒ×ÔÖÓÖÑØ
Page 33 and 34: ÌÖÒ×ÓÖÑØÓÒÅØÓÓÐÓÝ
Page 35 and 36: ÙÖ¿º¾ÖÐÓÔÓÒØ×ÖÐÝÖ
Page 37 and 38: ¿º¿ ×Ù×ØÓØÖÒ×ÖÓÖ×º
Page 39 and 40: Fluid Grid Node−1,1η1,1(x,y)(ξ,
Page 41 and 42: ÕÙØÓÒ¿º¾ÒÙ×ÓÒÐÝØÒ
Page 43 and 44: ÁØÛ×ÓÙÒÒ℄ØØØÐÒÖ×Ø
Page 45 and 46: BBPÙÖ¿ºËÖ××ÛÒÔÐÒÔÖÓ
Page 47 and 48: X1s,kPurely translated fictitious p
Page 49: Structural ComponentLevel 1 Mapping
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
Page 63 and 64: ÎÐØÓÒÓÖÓÖÐÔÅÓØÓÒ×
Page 65 and 66: ÙÖº½ÌÌÛÒØÙÒÒÐÑÓÐÛ
Page 67 and 68: º¾º¾ÌÆÄËËÌÖÖÓÛÏÒ Ù
Page 69 and 70: WingDeflected flapØØØÖÙÖÕÙ
Page 71 and 72: ÐÒ¸ØÛÒØÔÒÐ×ÓÖÓÙÒØ
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
Page 87 and 88: ÓÒØÖÓÐËÙÖÁÒ×ØÐØÝ Ô
Page 89 and 90: ÅÓ ÏÒÒÒ ÐÔÇ×ÐÐØÓÒ ½
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
Page 109 and 110:
ÌÖ×ØÖÑÚÐÓØÝ×½¾Ñ»×
Page 111 and 112:
×ØÖÙÖÕÙÒÝÚÒÝ¾ ÛÖØ×
Page 113 and 114:
ÌÀÛÖÖØ½ ÔØÖº½ ÁØ×Ò
Page 115 and 116:
ÐÙÐØÓÒ¸ØØÑ×ÛÖ×ÓÒ×
Page 117 and 118:
ÙÖº¿Ù×ÐÜÙÖÐÜ×ÛØØ
Page 119 and 120:
ÖÕÙÒÝÀÞ℄ ½¾º¾ ½º¾
Page 121 and 122:
× ÓÑØÔ ÏÒÛØÔ¼Æ ½¾
Page 123 and 124:
×ÐÐÓÛº ÚØÝ×ÓØÔÐÒ×
Page 125 and 126:
ÅÓ½½¾º ÅÓ¾¿º ÖÕÙÒÝ
Page 127 and 128:
CFDNastranDynamic pressureBuzz regi
Page 129 and 130:
ÙÖº½ØØÓÛÐÐÐÓÒØÔ
Page 131 and 132:
ÖÖØ¸ÒÒØ×ÖÙ×ÓÖØÐÙÐ
Page 133 and 134:
The Hawk Body-Fin-Wing-Rudder CaseO
Page 135 and 136:
ÅÖÖÓÖÒÓÅÓ× ÌØÖØÑÒØ
Page 137 and 138:
×½½½Æ ×¾ ÁÒÒÅÒÙÑÖ ¼
Page 139 and 140:
ÓÖØÖ××ÓÒÖ×ÒÓÑØÖÓÑ
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
Page 151 and 152:
ÛÖÒÓØÔÖØÝØÙÐÖÕÙØÓ
Page 153 and 154:
ÓÒØÖÓÐÐÛÒÓÖÑØÓÒ×Ò
Page 155 and 156:
½℄ÆËÙÓÑÑØØÓÒÎÖØÓÒ
Page 157 and 158:
℄ÃºÊÓÙÒ¸ÅºÖÒÌºÓÖØ
Page 159 and 160:
℄ºÃÖÐ××ÓÒÒºÏÒÞÐÐº
show all

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

You also want an ePaper? Increase the reach of your titles

Delete template?

Save as template?