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Lift Coefficient Predictions for Delta Wing Under Pitching Motions
Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems. Linköping University, The Institute of Technology.
Linköping University, Department of Management and Engineering, Machine Design. Linköping University, The Institute of Technology.
2002 (English)In: 32nd AIAA Fluid Dynamics Conference Proceedings (2002), USA: AIAA , 2002, AIAA-2002-2969- p.Conference paper, Published paper (Refereed)
Abstract [en]

An analytic prediction method is presented to estimate the lift coefficient of delta wings under pitching motions. The method is based on the leading edge suction analogy, with regards to the dynamic effect resulting in the unsteady behaviour. The goal of the method is to provide suitable lift equation for use in simulation in preliminary design.

Place, publisher, year, edition, pages
USA: AIAA , 2002. AIAA-2002-2969- p.
National Category
Engineering and Technology
Identifiers
URN: urn:nbn:se:liu:diva-40982DOI: 10.2514/6.2002-2969Local ID: 54814OAI: oai:DiVA.org:liu-40982DiVA: diva2:261832
Conference
32nd AIAA Fluid Dynamics Conference. 24 June 2002 - 26 June 2002. St. Louis, Missouri.
Available from: 2009-10-10 Created: 2009-10-10 Last updated: 2013-12-12
In thesis
1. Modelling of unsteady aerodynamics for aircraft design
Open this publication in new window or tab >>Modelling of unsteady aerodynamics for aircraft design
2003 (English)Licentiate thesis, comprehensive summary (Other academic)
Abstract [en]

This thesis present a simple mathematical prediction model for high angles of attack aerodynamics, including dynamic effects over delta wings, and an extension to full configuration. The model presented is intended for application in conceptual design and is extended to parameters identifications in preliminary design with validation against experimental data.

The aerodynamic model is based on leading edge suction analogy. In order to extend it to high angles of attack and dynamic motions, internal state variables are used to describe the different flow conditions, or state, over the wing/aircraft.

In conceptual design the parameters used are determined from geometrical considerations and analogies with delta wings. For slender delta wings, the parameters are determined from flow visualisation, determining the three transition states used here; potential, vortex and fully separated. Results from conceptual design have shown good agreement with published data and demonstrates the usefulness of integration of dynamic effects in aerodynamic predictions. To extend the mathematical model to later design phases and augment the accuracy, the parameters were determined from wind tunnel data. The results obtained then showed high accuracy in both static and dynamic cases.

The results obtained both in conceptual design and from parameters identifications are suitable for flight simulation and stability analyses, and will allow the aircraft designer to increase his knowledge of the behaviour at high angles of attack and large pitch motions. The present model allows to keep the same mathematical structure through the entire design, the parameters being refined when new data is available from wind tunnel tests or CDF or flight tests.

The present model will be included in a distributed aircraft analyse to simulate the whole aircraft including systems and sub-systems.

Place, publisher, year, edition, pages
Linköping: Linköpings universitet, 2003. 71 p.
Series
Linköping Studies in Science and Technology. Thesis, ISSN 0280-7971 ; 1053
Keyword
Aircraft Deisgn, Aerodynamic
National Category
Engineering and Technology
Identifiers
urn:nbn:se:liu:diva-40992 (URN)54827 (Local ID)91-7373-769-0 (ISBN)54827 (Archive number)54827 (OAI)
Available from: 2009-10-10 Created: 2009-10-10 Last updated: 2013-12-12

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Jouannet, ChristopherKrus, Petter

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CiteExportLink to record
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Citation style
  • apa
  • harvard1
  • ieee
  • modern-language-association-8th-edition
  • vancouver
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  • Other style
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  • Other locale
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Output format
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  • asciidoc
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