Rotational compressible inverse design method for two-dimensional, internal flow configurations

Dedoussis, V; Chaviaropoulos, P; Papailiou, KD

dc.contributor.author	Dedoussis, V	en
dc.contributor.author	Chaviaropoulos, P	en
dc.contributor.author	Papailiou, KD	en
dc.date.accessioned	2014-03-01T01:09:31Z
dc.date.available	2014-03-01T01:09:31Z
dc.date.issued	1993	en
dc.identifier.issn	0001-1452	en
dc.identifier.uri	https://dspace.lib.ntua.gr/xmlui/handle/123456789/11057
dc.subject	Design Method	en
dc.subject.classification	Engineering, Aerospace	en
dc.subject.other	Integration	en
dc.subject.other	Clebsch formulation	en
dc.subject.other	Frenet equations	en
dc.subject.other	Potential function/stream function formulation	en
dc.subject.other	Rotational compressible inverse design method	en
dc.subject.other	Thermal drift function	en
dc.subject.other	Compressible flow	en
dc.subject.other	Ducts, Nozzles	en
dc.subject.other	Internal Flow	en
dc.subject.other	Two-Phase Flow	en
dc.title	Rotational compressible inverse design method for two-dimensional, internal flow configurations	en
heal.type	journalArticle	en
heal.identifier.primary	10.2514/3.11364	en
heal.identifier.secondary	http://dx.doi.org/10.2514/3.11364	en
heal.language	English	en
heal.publicationDate	1993	en
heal.abstract	The development of a rotational inviscid compressible inverse design method for two-dimensional internal flow configurations is described. Rotationality is due to incoming entropy gradient whereas total enthalpy is considered to be constant throughout the flowfield. The method is based on the potential function/stream function formulation. The Ciebsch formulation is adopted to decompose the velocity vector into a potential and a rotational part. The physical space on which the boundaries of the flowfield are sought is mapped onto the (phi, psi) space via a body-fitted coordinate transformation. A novel procedure based on differential geometry arguments is employed to derive the governing equation for the velocity. The velocity equation solved in conjunction with a transport equation for a thermal drift function provide the flowfield without any geometry feedback. An auxiliary orthogonal computational grid adapted to the solution is employed. Geometry is determined by integrating Frenet equations of the grid lines. Inverse calculation results are compared with results of direct ''reproduction'' calculations.	en
heal.publisher	AMER INST AERONAUT ASTRONAUT	en
heal.journalName	AIAA journal	en
dc.identifier.doi	10.2514/3.11364	en
dc.identifier.isi	ISI:A1993KU60600020	en
dc.identifier.volume	31	en
dc.identifier.issue	3	en
dc.identifier.spage	551	en
dc.identifier.epage	558	en