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Finite-volume scheme for the solution of integral boundary layer equations
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering. (Flight Dynamics)ORCID iD: 0000-0003-1604-4262
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering. (Flight Dynamics)ORCID iD: 0000-0002-3199-8534
2016 (English)In: Computers & Fluids, ISSN 0045-7930, E-ISSN 1879-0747, Vol. 132, 62-71 p.Article in journal (Refereed) Published
Resource type
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.

Place, publisher, year, edition, pages
Elsevier, 2016. Vol. 132, 62-71 p.
Keyword [en]
Embedded surfaces, Finite-volume method, Integral boundary layer equations, Steady conservation laws, Unstructured meshes, Up-wind scheme
National Category
Other Engineering and Technologies not elsewhere specified
Identifiers
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: diva2:930149
Note

QC 20160523

Available from: 2016-05-23 Created: 2016-05-16 Last updated: 2017-08-16Bibliographically approved
In thesis
1. On Aerodynamic and Aeroelastic Modeling for Aircraft Design
Open this publication in new window or tab >>On Aerodynamic and Aeroelastic Modeling for Aircraft Design
2017 (English)Doctoral thesis, comprehensive summary (Other academic)
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.

Place, publisher, year, edition, pages
KTH Royal Institute of Technology, 2017. 27 p.
Series
TRITA-AVE, ISSN 1651-7660 ; 2017:44
Keyword
viscous-inviscid interaction model, laminar flow wing, aerodynamics, aeroelasticity, aircraft design
National Category
Engineering and Technology
Research subject
Aerospace Engineering
Identifiers
urn:nbn:se:kth:diva-212051 (URN)978-91-7729-480-1 (ISBN)
Public defence
2017-09-22, F3, Lindstedtsvägen 26, Stockholm, 14:00 (English)
Opponent
Supervisors
Note

QC 20170816

Available from: 2017-08-16 Created: 2017-08-15 Last updated: 2017-08-16Bibliographically approved

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