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Implementation and Verification of a Correlation Based Transition Prediction Method
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Aerodynamics.
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Aerodynamics.
2008 (English)In: 38th Fluid Dynamics Conference and Exhibit, American Institute of Aeronautics and Astronautics, 2008Conference paper, Published paper (Refereed)
Abstract [en]

In many applications such as turbine and aircraft design, boundary layer transition prediction is an important topic. This paper deals with the implementation and verification of a correlation based transition prediction method previously presented by Menter and Langtry. The two additional transport equations used for predicting transition and a novel set of equations for the production terms are implemented into the CFD code Edge. The results are compared to the well-known Ercoftac wind tunnel results.

Place, publisher, year, edition, pages
American Institute of Aeronautics and Astronautics, 2008.
Keyword [en]
Aircraft design, Boundary layer transitions, CFD codes, Transition prediction methods, Transport equation
National Category
Vehicle Engineering
Identifiers
URN: urn:nbn:se:kth:diva-9250Scopus ID: 2-s2.0-78049490178OAI: oai:DiVA.org:kth-9250DiVA: diva2:37742
Conference
38th AIAA Fluid Dynamics Conference and Exhibit; Seattle, WA; United States; 23 June 2008 through 26 June 2008
Note

QC 20100903

Available from: 2008-10-13 Created: 2008-10-13 Last updated: 2017-03-21Bibliographically approved
In thesis
1. CFD Methods for Predicting Aircraft Scaling Effects
Open this publication in new window or tab >>CFD Methods for Predicting Aircraft Scaling Effects
2008 (English)Doctoral thesis, comprehensive summary (Other scientific)
Abstract [en]

This thesis deals with the problems of scaling aerodynamic data from wind tunnel to free flight  conditions. The main challenges when this scaling should be performed is how the model support, wall interference and the potentially lower Reynolds number in the windtunnel should be corrected. Computational Fluid Dynamics (CFD) simulations have been performed on a modern transonic transport aircraft in order to reveal Reynolds number effects and how these should be scaled accurately. A methodology for scaling drag and identifying scaling effects in general is presented.  This investigation also examines how the European Transonic Wind tunnel twin sting model support influences the flow over the aircraft. When the Reynolds number is differing between the wind tunnel and free flight conditions, a change in boundary layer transition position can occur. In order to estimate first order boundary layer transition effects a correlation based transition prediction method, previously presented by Menter and Langtry, is implemented in the CFD solver Edge. The transition model is further developed and a novel set of equations for the production terms is found through a CFD/optimizer coupling. The transition data, used to calibrate the CFD transition model,  have been extracted from a low Mach number wind tunnel campaign. At these low Mach numbers many compressible CFD solvers suffer of poor convergence rates and a deficiency in robustness and accuracy might appear. The low Mach number effects are investigated, and an effort to prevent these is done by implementing different preconditioning techniques in the compressible CFD solver Edge. The preconditioners are mainly based on the general Turkel preconditioner, but a novel formulation is also presented in order to make the numerical technique less problem dependent.

Place, publisher, year, edition, pages
Stockholm: KTH, 2008. vi, 26 p.
Series
Trita-AVE, ISSN 1651-7660 ; 2008:56
Keyword
CFD, Scaling Effects, Boundary Layer Transition, Preconditioning
National Category
Vehicle Engineering
Identifiers
urn:nbn:se:kth:diva-9209 (URN)978-91-7415-134-3 (ISBN)
Public defence
2008-10-24, D1, Lindstedtsvägen 17, KTH, 10:15 (English)
Opponent
Supervisors
Note
QC 20100903Available from: 2008-10-13 Created: 2008-10-06 Last updated: 2010-09-03Bibliographically approved

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Scopushttp://dx.doi.org/10.2514/6.2008-4401

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CiteExportLink to record
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Citation style
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Output format
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