A continuous adjoint method with objective function derivatives based on boundary integrals, for inviscid and viscous flows

Papadimitriou, DI; Giannakoglou, KC

dc.contributor.author	Papadimitriou, DI	en
dc.contributor.author	Giannakoglou, KC	en
dc.date.accessioned	2014-03-01T01:25:39Z
dc.date.available	2014-03-01T01:25:39Z
dc.date.issued	2007	en
dc.identifier.issn	0045-7930	en
dc.identifier.uri	https://dspace.lib.ntua.gr/xmlui/handle/123456789/17708
dc.subject	Adjoint Method	en
dc.subject	Entropy Generation	en
dc.subject	Objective Function	en
dc.subject	Unstructured Grid	en
dc.subject	Viscous Flow	en
dc.subject.classification	Computer Science, Interdisciplinary Applications	en
dc.subject.classification	Mechanics	en
dc.subject.other	EQUATIONS	en
dc.title	A continuous adjoint method with objective function derivatives based on boundary integrals, for inviscid and viscous flows	en
heal.type	journalArticle	en
heal.identifier.primary	10.1016/j.compfluid.2005.11.006	en
heal.identifier.secondary	http://dx.doi.org/10.1016/j.compfluid.2005.11.006	en
heal.language	English	en
heal.publicationDate	2007	en
heal.abstract	A continuous adjoint formulation for inverse design problems in external aerodynamics and turbomachinery is presented. The advantage of the proposed formulation is that the objective function gradient does not depend upon the variation of field geometrical quantities, such as metrics variations in the case of structured grids. The final expression for the objective function gradient includes only boundary integrals which can readily be calculated in both structured and unstructured grids; this is feasible in design problems where the objective function is either a boundary integral (pressure deviation along the solid walls) or a field integral (the entropy generation over the flow domain). The formulation governs inviscid and viscous flows; it takes into account the streamtube thickness variation terms in quasi-3D cascade designs or rotational terms in rotating blade design problems. The application of the method is illustrated through a number of design problems concerning isolated airfoils, a 3D duct, 2D, quasi-3D and 3D, stationary and rotating turbomachinery blades. (c) 2006 Elsevier Ltd. All rights reserved.	en
heal.publisher	PERGAMON-ELSEVIER SCIENCE LTD	en
heal.journalName	COMPUTERS & FLUIDS	en
dc.identifier.doi	10.1016/j.compfluid.2005.11.006	en
dc.identifier.isi	ISI:000242787400011	en
dc.identifier.volume	36	en
dc.identifier.issue	2	en
dc.identifier.spage	325	en
dc.identifier.epage	341	en