london rigid fune AH 1969 photograph experii cuiidition KE HANC share tween iscid CV patterson density lift inite source planform JL show skew 4200 tlescribing 700 panel iiiui circulatory 32X APPENDIX table 60o wll applicati wa set equating expression could application aer both speed gothic scribed parallelogram nodal downwiish 'ing direetion KORNECKI clamped approach absence behaved stlft'ncss dynamic appear rectangular derive equation boolean aerodynamic stiffnes exist natural transposed bond four iin affected ANOLE entire ilia represented idealisation simple differentiation vol crnploy leading calculation uriitoil departmental assembled finite numerical exact virtual tlif iion sirenmwiso presented concerning gular account little ated notation parameter relation combina sine say 1968 increase AROYRIS suggested wise published possible tting length miiorii elemental under frequencie move ronulta eho velocity motion angle clumped superior sistent permit ancl end theory particular cumbersome A0 isotropic archivc obtaini inihlifihi'il order data buckling vibration after A1C draining india KARIAPPA grammic matrice span DURVASUI colloquium smoke evaluation tier liquation conclusion wide anj orthotropic nnd jtf consistent iswrwlth jrj valuoc hoped compared characteristic continua extensive sake method kine any inal more stii material discontinua regarding 16XU slender jir cqn hat 560 measurement again ell'ort explained experiment HEARMON refer only accommodating structural drag convergence OF approache into good solved supersonic thicknes roll state 144 flat ooroach ihe hie introduction collapsed paper received unfortunately value and' displacement science iitera make big tip transformation applied function constant non ttt JOHNS society mechanic aspect vector elastic nwur aero illustrated variation SOMASHEKAH studying anil consider behaviour modes™ variou deflection studie liitmstin 484 generality occurred other JOUHNAL term except university principle criiical well inertial stiu'ncsse 1673 sharp cond displacements11 sociiity accomplished DURVASULA moda beam mall divided lumped oblique AGARD fig 196 air form give figure 4th lain lie cane derived scnled july may different mid svivhtr thu ary manage discrete number attempted hhuw test column 300 proved how relating having included pressure nura repented required also related but flrut over vortice agreement matrix undertaken include ha ving limiting ordinate ic—lip thesi based lern tingle unit made field ANGLE shape kincmatlcnlly edge breakdown nitiy combining programme computer time rcf ske quantitie geometry AIG eigenvalue serie complex nine 270 represent hei 'transformation element apart disagreement tin gradual clarity iguchi use tare theorie breal •the miirch pan con conference mentioned facility computation momentum ice observed 420 mean AR olrci kinematic tiknw tory a'a0 SKEW effect iero 12x1 s'c primary above help combined 19600 somasni'kan clement conven assi 1X12 practical brea reduce ol' inrgcr supported note there HANCOCK jugate certain occur reache sufflcie should TYPICAL accommo generalised CD interest MATRIX tskew coefficient proposed ami known era assumption shell dillerentialion straightforward davi'ni'ou result emotion solution detail matically deriving outside computed physical difficult JOURNAL comparison all british attain practically parallelo flutter limitation factor inertia including complete 1957 10' below 673 chosen 90o recently ui wright comment appendix assemble relative extended argument revise induced they 1668 presented1' mtal ably region according AIAA AUGUS approa TR showing snect satisfied 271 basic 840 excellent stillnes fluttei clireclion ahhonautical date conventional nevertheles ijft CK ohio NOTES model national stand dimensionul highly sntal on measured study uisplaccmt'iu case slight surface foi discontinuitie blow argyri about down 120 slilfnes defined formed own obtaining TABLE fit1 representing operation yield lli' achieved lin satisfactory KM face ease large tural stu boundary deformation XXXV long force measure become tilt 1964 lire tion UTIA AM lead plate modc 674 mechanism corresponding 12nd msc sviv fall work 402 640 whether three april reference straining two arbitrary each damping wherea technique it asses realistic available aoronnulloal scrie PN however double one minimum nutter clio emphasised laboratory considered IE KK january afntiunitwal eighth direction functioi dictating vertical problem camber SOMASIIHKAR ref pon journal ratio till then benertil ring due argued increased 1952 dimensional intensity VOL 'the ttnnfinloro nil same free merit here royal expressed rept given superiority ding analysi reynold sible HOYAI between delta attack publication circulation southampton 240 concise oorodynamlo body 1967 using single since critical gap ing namely nection literature clearly deformed coalesce derivation algebra written limited obtained elegantly obtain stream ELEMENT proceeding AERONAUTICAL capabilitie 7r't because condition intllit subscript symmetric siww covered smaller spite tit frequency JJ figura muy nay complicated experimental II vortex mach longer struc them originally used bou AIC incidence nautical tech trailing hence mode 29400 aeronautical SIUNIVASAN further base valu november influence kinematically reg statu superscript wing denote point assumed neglected ion measur flow briefly found masse aerospace UOI low theoretical BO linear geomotrieal visualisation lopological eigen nof once mil graph purpose ret inherent miu successful 1965 SO present see PHESI common applicability chord 1970 general maximum lia tlilliculty stage side tunnel yector OP attained mccokmick rectan fourier instance simply 1966 investigation dfd rigidity iircc bout uniquely noted 80MA8HEKAR along not 676 eqn circular live •mj before 403 vvinj high