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From geometry to CFD-based aerodynamic derivatives - an automated approach
KTH, Skolan för teknikvetenskap (SCI), Farkost och flyg, Aerodynamik.
KTH, Skolan för teknikvetenskap (SCI), Farkost och flyg.ORCID-id: 0000-0002-3199-8534
2010 (engelsk)Inngår i: 27th Congress of theInternaitonal Council of the Aeronautical Sciences, 19-24 Sept 2010, Nice, France: Volume 1, 2010, s. 762-774Konferansepaper, Publicerat paper (Fagfellevurdert)
sted, utgiver, år, opplag, sider
2010. s. 762-774
Emneord [en]
Automated analysis, CFD, Mesh generation
HSV kategori
Identifikatorer
URN: urn:nbn:se:kth:diva-31399Scopus ID: 2-s2.0-84878494661ISBN: 978-161782049-6 (tryckt)OAI: oai:DiVA.org:kth-31399DiVA, id: diva2:403505
Konferanse
27th Congress of the International Council of the Aeronautical Sciences 2010, ICAS 2010; Nice; France; 19 September 2010 through 24 September 2010
Merknad

QC 20110314

Tilgjengelig fra: 2011-03-14 Laget: 2011-03-14 Sist oppdatert: 2014-08-15bibliografisk kontrollert
Inngår i avhandling
1. Adaptive-fidelity CFD for predicting flying qualities in preliminary aircraft design
Åpne denne publikasjonen i ny fane eller vindu >>Adaptive-fidelity CFD for predicting flying qualities in preliminary aircraft design
2011 (engelsk)Licentiatavhandling, med artikler (Annet vitenskapelig)
Abstract [en]

To reduce development cost and to avoid late design fixes in aircraft design, methods that are fast and economic in estimating the aerodynamic characteristics of complex flight vehicles at the preliminary design stage are desired. This work and thesis focus on the adaptive-fidelity CFD approach, with emphasis on the high end of the CFD tools available today.

The core idea of the method is to use computationally cheap modeling in the part of the flight envelope where it is applicable. When the complexity in the flow field increases more details and realism is included in the mathematical model, at a computationally higher cost. A typical case where this would be required could be at the border of the flight envelope, where flow phenomena such as shocks, flow separation, and interacting vortex systems could occur.

Since the number of cases needed to resolve the flight envelope could be in the order of ten thousands automation is required. The bottlenecks are the discretization of the fluid volume and evaluation of raw CFD data and post processing of the data. These issues are also discussed in this work.

The method has been tested on two real flying aircraft, the X-31 delta-winged aircraft with vector thrust, and the Ranger 2000 Jet trainer, as well as on the SACCON preliminary wing-body UCAV design. The results provide improved understanding of the usefulness of this method as an analysis tool during the preliminary design phase all the way into the flight test diagnostic phase of a new aircraft.

 

sted, utgiver, år, opplag, sider
Stockholm: KTH Royal Institute of Technology, 2011. s. x, 23
Serie
Trita-AVE, ISSN 1651-7660 ; 2011:07
HSV kategori
Identifikatorer
urn:nbn:se:kth:diva-31400 (URN)
Presentation
2011-02-25, Sal H1, KTH, Teknikringen 33, Stockholm, 10:15 (engelsk)
Opponent
Veileder
Merknad
QC 20110314Tilgjengelig fra: 2011-03-14 Laget: 2011-03-14 Sist oppdatert: 2011-03-14bibliografisk kontrollert

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