Abstract111 this paper, we rcvicw the d e v e l o l~n~e~~t of new reducecl-orcler ~r~o t l e l i~~g tecl~niques ant1 tliscuss their applicalrility to variolts prol)len~s in co~ril)utatior~ul pl~ysics. Eu~pllasis is gi~.cn to r~~ctho(ls basetl 011 j'olterra series r e l ) r e s e~~t a t i o~~s and thr proper ortllogo11a1 deco~~~position. Results are reported for cliffcre~~t 11ol11i11ear systct~l~s to 1)rovidc clear cxan~ples of the cor~struc.tio~~ a11t1 usc of recluc~cd-orcler rllod(>ls, p;lrtic.-ularly ill the 1l11tlti-cliscil)li11:1ry field of c o~~~l ) u t a t i o~~a l aeroelasticity. U~~s t e a d y aerodj,nan~ic and aeroelast,ic behaviors of two-di~nrnsional and three-dinle~~sional g e o~~~e t r i e s arc. tlcscri1)etl. Large illcreases in co1111)utational efficie~~c,y are ol~t,:ii~lccl thruugl~ the use of rcducetl-order ~r~otlc!ls! thcrebj. justifying the izlitial c.onlputatio11a1 esl)c:~~se of constructing th(:sr r~~oticls and ~~~o t i v a t i r~g tl~eir usc for ~~~ulti-disc,i[)Ii~la~>. design analysis.
A significant improvement to the development of CFD-based unsteady aerodynamic reduced-order models (ROMs) is presented. This improvement involves the simultaneous excitation of the structural modes of the CFD-based unsteady aerodynamic system that enables the computation of the unsteady aerodynamic state-space model using a single CFD execution, independent of the number of structural modes. Four different types of inputs are presented that can be used for the simultaneous excitation of the structural modes. Results are presented for a flexible, supersonic semi-span configuration using the CFL3Dv6.4 code.
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