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Finite-volume scheme for the solution of integral boundary layer equations
KTH, Skolan för teknikvetenskap (SCI), Farkost och flyg. (Flight Dynamics)ORCID-id: 0000-0003-1604-4262
KTH, Skolan för teknikvetenskap (SCI), Farkost och flyg. (Flight Dynamics)ORCID-id: 0000-0002-3199-8534
2016 (engelsk)Inngår i: Computers & Fluids, ISSN 0045-7930, E-ISSN 1879-0747, Vol. 132, s. 62-71Artikkel i tidsskrift (Fagfellevurdert) Published
Resurstyp
Text
Abstract [en]

An unstructured-mesh finite-volume formulation for the solution of systems of steady conservation laws on embedded surfaces is presented. The formulation is invariant to the choice of local tangential coordinate systems and is stabilized by a novel up-winding scheme applicable also to mixed-hyperbolic systems. The formulation results in a system of non-linear equations which is solved by a quasi-Newton method. While the finite volume scheme is applicable to a range of conservation laws, it is here implemented for the solution of the integral boundary layer equations, as a first step in developing a fully coupled viscous-inviscid interaction method. For validation purposes, integral boundary layer quantities computed using a minimal set of three-dimensional turbulent integral boundary layer equations are compared to experimental data and an established computer code for two-dimensional problems. The validation shows that the proposed formulation is stable, yields a well-conditioned global Jacobian, is conservative on curved surfaces and invariant to rotation as well as convergent with regard to mesh refinement.

sted, utgiver, år, opplag, sider
Elsevier, 2016. Vol. 132, s. 62-71
Emneord [en]
Embedded surfaces, Finite-volume method, Integral boundary layer equations, Steady conservation laws, Unstructured meshes, Up-wind scheme
HSV kategori
Identifikatorer
URN: urn:nbn:se:kth:diva-186926DOI: 10.1016/j.compfluid.2016.04.002ISI: 000375814700007Scopus ID: 2-s2.0-84962911736OAI: oai:DiVA.org:kth-186926DiVA, id: diva2:930149
Merknad

QC 20160523

Tilgjengelig fra: 2016-05-23 Laget: 2016-05-16 Sist oppdatert: 2017-08-16bibliografisk kontrollert
Inngår i avhandling
1. On Aerodynamic and Aeroelastic Modeling for Aircraft Design
Åpne denne publikasjonen i ny fane eller vindu >>On Aerodynamic and Aeroelastic Modeling for Aircraft Design
2017 (engelsk)Doktoravhandling, med artikler (Annet vitenskapelig)
Abstract [en]

The work presented in this thesis was performed with the aim of developing improved prediction methods for aerodynamic and aeroelastic analysis to be used in aircraft design. The first part of the thesis concerns the development of a viscous-inviscid interaction model for steady aerodynamic predictions. Since an inviscid, potential flow, model already is available, the main focus is on the development of a viscous model consisting of a three-dimensional integral boundary layer model. The performance of the viscous-inviscid interaction model is evaluated and it is found that the accuracy of the predictions as well as the computational cost appear to be acceptable for the intended application. The presented work also includes an experimental study aimed at analyzing steady and unsteady aerodynamic characteristics of a laminar flow wing model. An enhanced understanding of these characteristics is presumed to be useful for the development of improved aerodynamic prediction models. A combination of nearly linear as well as clearly nonlinear aerodynamic variations are observed in the steady as well as in the unsteady experimental results and it is discussed how these may relate to boundary layer properties as well as to aeroelastic stability characteristics. Aeroelastic considerations are receiving additional attention in the thesis, as a method for prediction of how flutter characteristics are affected by modeling uncertainties is part of the presented material. The analysis method provides an efficient alternative for obtaining increased information about, as well as enhanced understanding of, aeroelastic stability characteristics.

sted, utgiver, år, opplag, sider
KTH Royal Institute of Technology, 2017. s. 27
Serie
TRITA-AVE, ISSN 1651-7660 ; 2017:44
Emneord
viscous-inviscid interaction model, laminar flow wing, aerodynamics, aeroelasticity, aircraft design
HSV kategori
Forskningsprogram
Flyg- och rymdteknik
Identifikatorer
urn:nbn:se:kth:diva-212051 (URN)978-91-7729-480-1 (ISBN)
Disputas
2017-09-22, F3, Lindstedtsvägen 26, Stockholm, 14:00 (engelsk)
Opponent
Veileder
Merknad

QC 20170816

Tilgjengelig fra: 2017-08-16 Laget: 2017-08-15 Sist oppdatert: 2017-08-16bibliografisk kontrollert

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