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
Reynolds number effects identified with CFD methods compared to semi-empirical methods
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Aerodynamics.
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Aerodynamics.
2006 (English)In: ICAS-Secretariat - 25th Congress of the International Council of the Aeronautical Sciences 2006, Curran Associates, Inc., 2006, Vol. 3, 1566-1579 p.Conference paper, Published paper (Refereed)
Abstract [en]

In order to estimate Reynolds number effects on a transonic transport aircraft CFD calculations have been performed. The CFD calculations have been done solving the RANS equations on an unstructured grid for varying Reynolds number at transonic conditions. Low Reynolds number data have been extrapolated to a higher Reynolds number condition with different scaling methodologies in order to evaluate each methods strengths and weaknesses.

Place, publisher, year, edition, pages
Curran Associates, Inc., 2006. Vol. 3, 1566-1579 p.
Keyword [en]
Aeronautics, CFD, Corrections, Reynolds number, Scaling
National Category
Vehicle Engineering
Identifiers
URN: urn:nbn:se:kth:diva-6183Scopus ID: 2-s2.0-84896998317OAI: oai:DiVA.org:kth-6183DiVA: diva2:10821
Conference
25th Congress of the International Council of the Aeronautical Sciences 2006, Hamburg, Germany, 3 September 2006 through 8 September 2006
Note

QC 20100903

Available from: 2006-10-03 Created: 2006-10-03 Last updated: 2015-04-14Bibliographically approved
In thesis
1. Scaling techniques using CFD and wind tunnel measurements for use in aircraft design
Open this publication in new window or tab >>Scaling techniques using CFD and wind tunnel measurements for use in aircraft design
2006 (English)Licentiate thesis, comprehensive summary (Other scientific)
Abstract [en]

This thesis deals with the problems of scaling aerodynamic data from wind tunnel conditions to free flight. The main challenges when this scaling should be performed is how the model support, wall interference and the potentially lower Reynolds number in the wind tunnel 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. This investigation also examined how the European Transonic Wind tunnel (ETW) twin sting model support influences the flow over the aircraft. In order to further examine Reynolds number effects a MATLAB based code capable of extracting local boundary layer properties from structured and unstructured CFD calculations have been developed and validated against wind tunnel measurements. A general scaling methodology is presented.

Place, publisher, year, edition, pages
Stockholm: KTH, 2006. xii, 17 p.
Series
Trita-AVE, ISSN 1651-7660 ; 2006:64
Keyword
CFD, wind tunnel, scaling, Reynolds number effect
National Category
Vehicle Engineering
Identifiers
urn:nbn:se:kth:diva-4122 (URN)
Presentation
2006-10-13, S40, Teknikringen 8, Stockholm, 10:00
Opponent
Supervisors
Note
QC 20101123Available from: 2006-10-03 Created: 2006-10-03 Last updated: 2010-11-23Bibliographically approved
2. 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

Open Access in DiVA

No full text

Scopus

Search in DiVA

By author/editor
Pettersson, KarlRizzi, Arthur
By organisation
Aerodynamics
Vehicle Engineering

Search outside of DiVA

GoogleGoogle Scholar

urn-nbn

Altmetric score

urn-nbn
Total: 242 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