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Time-resolved Adaptive Direct FEM Simulation of High-lift Aircraft Configurations: Chapter in "Numerical Simulation of the Aerodynamics of High-Lift Configurations'", Springer
KTH, Skolan för datavetenskap och kommunikation (CSC), Beräkningsvetenskap och beräkningsteknik (CST).
(BCAM - Basque Center for Applied Mathematics)
KTH, Skolan för datavetenskap och kommunikation (CSC), Beräkningsvetenskap och beräkningsteknik (CST). (BCAM - Basque Center for Applied Mathematics)
KTH, Skolan för datavetenskap och kommunikation (CSC), Beräkningsvetenskap och beräkningsteknik (CST).
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2018 (Engelska)Ingår i: Numerical Simulation of the Aerodynamics of High-Lift Configurations / [ed] Omar Darío López Mejia andJaime A. Escobar Gomez, Springer, 2018, s. 67-92Kapitel i bok, del av antologi (Refereegranskat)
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.

Ort, förlag, år, upplaga, sidor
Springer, 2018. s. 67-92
Nationell ämneskategori
Beräkningsmatematik
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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 (digital)ISBN: 978-3-319-62135-7 (tryckt)OAI: oai:DiVA.org:kth-211705DiVA, id: diva2:1130499
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QC 20180821

Tillgänglig från: 2017-08-09 Skapad: 2017-08-09 Senast uppdaterad: 2018-11-21Bibliografiskt granskad

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Förlagets fulltextScopushttps://link.springer.com/chapter/10.1007/978-3-319-62136-4_5

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Jansson, JohanLeoni, MassimilianoJansson, NiclasHoffman, Johan
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