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Scaling techniques using CFD and wind tunnel measurements for use in aircraft design
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
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 [en]
CFD, wind tunnel, scaling, Reynolds number effect
National Category
Vehicle Engineering
Identifiers
URN: urn:nbn:se:kth:diva-4122OAI: oai:DiVA.org:kth-4122DiVA: diva2:10823
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
List of papers
1. Estimating Reynolds number scaling and windtunnel boom effects with the help of CFD methods
Open this publication in new window or tab >>Estimating Reynolds number scaling and windtunnel boom effects with the help of CFD methods
2006 (English)In: Collection of Technical Papers - AIAA Applied Aerodynamics Conference, 2006, 889-895 p.Conference paper, Published paper (Refereed)
Abstract [en]

In order to estimate the aerodynamic effects of the twin sting booms in the European Transonic Wind Tunnel (ETW) 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 the aircraft with and without booms mounted and for varying Reynolds number. The two sets of data (booms on and booms off) enables comparisons, isolating booms and Reynolds number effects and conclusions can be drawn. These conclusions might give information about how the free flight aircraft would differ from the wind tunnel data.

Keyword
Computational fluid dynamics, Data structures, Supersonic aircraft, Transport aircraft, Wind tunnels
National Category
Vehicle Engineering
Identifiers
urn:nbn:se:kth:diva-6182 (URN)2-s2.0-33845389026 (Scopus ID)978-156347812-3 (ISBN)
Conference
24th AIAA Applied Aerodynamics Conference; San Francisco, CA; 5 June 2006 through 8 June 2006
Note
QC 20101123Available from: 2006-10-03 Created: 2006-10-03 Last updated: 2010-11-23Bibliographically approved
2. Reynolds number effects identified with CFD methods compared to semi-empirical methods
Open this publication in new window or tab >>Reynolds number effects identified with CFD methods compared to semi-empirical methods
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
Keyword
Aeronautics, CFD, Corrections, Reynolds number, Scaling
National Category
Vehicle Engineering
Identifiers
urn:nbn:se:kth:diva-6183 (URN)2-s2.0-84896998317 (Scopus ID)
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
3. Estimating local boundary layer properties using CFD and wind tunnel measurements
Open this publication in new window or tab >>Estimating local boundary layer properties using CFD and wind tunnel measurements
(English)Manuscript (Other academic)
National Category
Vehicle Engineering
Identifiers
urn:nbn:se:kth:diva-6184 (URN)
Note
QC 20101123Available from: 2006-10-03 Created: 2006-10-03 Last updated: 2010-11-23Bibliographically approved

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CiteExportLink to record
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Citation style
  • apa
  • harvard1
  • ieee
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  • vancouver
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  • Other locale
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Output format
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