Compressible flow airfoil design using natural coordinates

Chaviaropoulos, P; Dedoussis, V; Papailiou, KD

dc.contributor.author	Chaviaropoulos, P	en
dc.contributor.author	Dedoussis, V	en
dc.contributor.author	Papailiou, KD	en
dc.date.accessioned	2014-03-01T01:09:19Z
dc.date.available	2014-03-01T01:09:19Z
dc.date.issued	1993	en
dc.identifier.issn	0045-7825	en
dc.identifier.uri	https://dspace.lib.ntua.gr/xmlui/handle/123456789/10907
dc.subject	Compressible Flow	en
dc.subject.classification	Engineering, Multidisciplinary	en
dc.subject.classification	Mathematics, Interdisciplinary Applications	en
dc.subject.classification	Mechanics	en
dc.subject.other	Aerodynamics	en
dc.subject.other	Compressible flow	en
dc.subject.other	Conformal mapping	en
dc.subject.other	Inverse problems	en
dc.subject.other	Mathematical models	en
dc.subject.other	Mathematical transformations	en
dc.subject.other	Numerical analysis	en
dc.subject.other	Compressible flow airfoil design	en
dc.subject.other	Irrotational inviscid compressible inverse design method	en
dc.subject.other	Natural coordinates	en
dc.subject.other	Airfoils	en
dc.title	Compressible flow airfoil design using natural coordinates	en
heal.type	journalArticle	en
heal.identifier.primary	10.1016/0045-7825(93)90024-R	en
heal.identifier.secondary	http://dx.doi.org/10.1016/0045-7825(93)90024-R	en
heal.language	English	en
heal.publicationDate	1993	en
heal.abstract	An irrotational inviscid compressible inverse design method for two-dimensional airfoil profiles is described. The potential (phi) and streamfunction (psi) are used as the independent natural coordinates. The physical space on which the boundaries of the airfoil 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 equations for the inverse problem, by requiring the curvature of the flat 2-D Euclidean space to be zero. An auxiliary coordinate transformation permits the definition of C-type computational grids on the (phi, psi) plane resulting in a more accurate description of the leading edge region. Geometry is determined by integrating Frenet equations along the grid lines. A two-parameter iterative scheme has been incorporated in the design procedure in order to assure closure of the trailing edge. To validate the method, inverse calculation results are compared with direct, 'reproduction', calculation results. The design procedure of a new airfoil shape is also presented.	en
heal.publisher	ELSEVIER SCIENCE SA LAUSANNE	en
heal.journalName	Computer Methods in Applied Mechanics and Engineering	en
dc.identifier.doi	10.1016/0045-7825(93)90024-R	en
dc.identifier.isi	ISI:A1993MP82900010	en
dc.identifier.volume	110	en
dc.identifier.issue	1-2	en
dc.identifier.spage	131	en
dc.identifier.epage	142	en