Change search
CiteExportLink to record
Permanent link

Direct link
Cite
Citation style
  • apa
  • harvard1
  • ieee
  • modern-language-association-8th-edition
  • vancouver
  • Other style
More styles
Language
  • de-DE
  • en-GB
  • en-US
  • fi-FI
  • nn-NO
  • nn-NB
  • sv-SE
  • Other locale
More languages
Output format
  • html
  • text
  • asciidoc
  • rtf
Time-resolved Adaptive Direct FEM Simulation of High-lift Aircraft Configurations: Chapter in "Numerical Simulation of the Aerodynamics of High-Lift Configurations'", Springer
KTH, School of Computer Science and Communication (CSC), Computational Science and Technology (CST).
(BCAM - Basque Center for Applied Mathematics)
KTH, School of Computer Science and Communication (CSC), Computational Science and Technology (CST). (BCAM - Basque Center for Applied Mathematics)
KTH, School of Computer Science and Communication (CSC), Computational Science and Technology (CST).
Show others and affiliations
2018 (English)In: Numerical Simulation of the Aerodynamics of High-Lift Configurations / [ed] Omar Darío López Mejia andJaime A. Escobar Gomez, Springer, 2018, p. 67-92Chapter in book (Refereed)
Abstract [en]

We present an adaptive finite element method for time-resolved simulation of aerodynamics without any turbulence-model parameters, which is applied to a benchmark problem from the HiLiftPW-3workshop to compute the flowpast a JAXA Standard Model (JSM) aircraft model at realistic Reynolds numbers. The mesh is automatically constructed by the method as part of an adaptive algorithm based on a posteriori error estimation using adjoint techniques. No explicit turbulence model is used, and the effect of unresolved turbulent boundary layers is modeled by a simple parametrization of the wall shear stress in terms of a skin friction. In the case of very high Reynolds numbers, we approximate the small skin friction by zero skin friction, corresponding to a free-slip boundary condition, which results in a computational model without any model parameter to be tuned, and without the need for costly boundary-layer resolution. We introduce a numerical tripping-noise term to act as a seed for growth of perturbations; the results support that this triggers the correct physical separation at stall and has no significant pre-stall effect. We show that the methodology quantitavely and qualitatively captures the main features of the JSM experiment-aerodynamic forces and the stall mechanism-with a much coarser mesh resolution and lower computational cost than the state-of-the-art methods in the field, with convergence under mesh refinement by the adaptive method. Thus, the simulation methodology appears to be a possible answer to the challenge of reliably predicting turbulent-separated flows for a complete air vehicle.

Place, publisher, year, edition, pages
Springer, 2018. p. 67-92
National Category
Computational Mathematics
Identifiers
URN: urn:nbn:se:kth:diva-211705DOI: 10.1007/978-3-319-62136-4_5Scopus ID: 2-s2.0-85053970698ISBN: 978-3-319-62136-4 (electronic)ISBN: 978-3-319-62135-7 (print)OAI: oai:DiVA.org:kth-211705DiVA, id: diva2:1130499
Note

QC 20180821

Available from: 2017-08-09 Created: 2017-08-09 Last updated: 2018-11-21Bibliographically approved

Open Access in DiVA

No full text in DiVA

Other links

Publisher's full textScopushttps://link.springer.com/chapter/10.1007/978-3-319-62136-4_5

Search in DiVA

By author/editor
Jansson, JohanLeoni, MassimilianoJansson, NiclasHoffman, Johan
By organisation
Computational Science and Technology (CST)
Computational Mathematics

Search outside of DiVA

GoogleGoogle Scholar

doi
isbn
urn-nbn

Altmetric score

doi
isbn
urn-nbn
Total: 310 hits
CiteExportLink to record
Permanent link

Direct link
Cite
Citation style
  • apa
  • harvard1
  • ieee
  • modern-language-association-8th-edition
  • vancouver
  • Other style
More styles
Language
  • de-DE
  • en-GB
  • en-US
  • fi-FI
  • nn-NO
  • nn-NB
  • sv-SE
  • Other locale
More languages
Output format
  • html
  • text
  • asciidoc
  • rtf