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Influences of unsteady aerodynamic in conceptual design
Linköping University, Department of Management and Engineering. Linköping University, The Institute of Technology.
Linköping University, Department of Management and Engineering. Linköping University, The Institute of Technology.
(English)Manuscript (preprint) (Other academic)
Abstract [en]

Integration of unsteady and high-angles aerodyuamics is often done late in aircraft design. An attempt to integrate these aspects in conceptual and preliminary design is presented here. A simple aerodynamic model has been developed and used in conceptual design to study the influences of dynamic effects on platform geometry during high angular rate manoeuvres. In order to include these effects in conceptual design, flight simulation has been coupled with classic sizing and turn rate performance is included in the requirements for conceptual sizing. In one case, the sizing and simulation are performed with static aerodynamics, in the other case dynamic effects are included . The impact of large augular rate and its significance for open loop simulation is presented in the form of a pitch up manoeuver.

National Category
Engineering and Technology
Identifiers
URN: urn:nbn:se:liu:diva-86277OAI: oai:DiVA.org:liu-86277DiVA: diva2:576209
Available from: 2012-12-12 Created: 2012-12-12 Last updated: 2012-12-12
In thesis
1. Model based aircraft design: high angle of attack aerodynamics and weight estimation methods
Open this publication in new window or tab >>Model based aircraft design: high angle of attack aerodynamics and weight estimation methods
2005 (English)Doctoral thesis, comprehensive summary (Other academic)
Abstract [en]

This thesis addresses modelling of high angle of attack aerodynamic characteristics and weight estimation for highly maneuverable aircraft during conceptual design. In order to allow configuration selection with sufficient confidence, especially with unconventional configurations, high angle of attack aerodynamic prediction and weight estimations methods need to be improved. In this thesis, a state-space variable approach is proposed for modelling high angle of attack aerodynamics including large angular rates. A new weight estimation based on a parametrical CAD model is also proposed.

The aerodynamic model is intended for use in both conceptual design and in later design phases. In conceptual design, the parameters are defined from geometrical data. Good results have been obtained with slender delta wings and on in various full configurations. When test data or CFD data arc available, the parameters are obtained from identification. Various results are presented with high accuracy iu the model. The developed model has been implemented in flight simulation, and in a sizing example, where two different aerodynamic models were used in order to show the influences of large angular rates on the geometrical layout. The presented weight estimation method is based on parametrical CAD models, and the weight is extracted from the structure layout. This allows any type of a ircraft configuration to be investigated, without the use of empirical or statistical approaches. Comparison with known aircraft has shown good agreement.

This thesis introduces a new aerodynamic model that includes large angular rates at any angle of attack, and a new weight prediction method. Both have shown good agreement with compared data and indicate that the models are suitable for conceptual design and that further studies should be conducted in order to extend the possibilities demonstrated here.

Place, publisher, year, edition, pages
Linköping: Linköpings universitet, 2005. 140 p.
Series
Linköping Studies in Science and Technology. Dissertations, ISSN 0345-7524 ; 968
National Category
Engineering and Technology
Identifiers
urn:nbn:se:liu:diva-31437 (URN)17220 (Local ID)91-85457-18-3 (ISBN)17220 (Archive number)17220 (OAI)
Public defence
2005-12-02, Nobel salen, Hus B, Linköpings Universitet, Linköping, 10:15 (Swedish)
Opponent
Available from: 2009-10-09 Created: 2009-10-09 Last updated: 2012-12-12

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Jouannet, ChristopherKrus, Petter

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CiteExportLink to record
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Citation style
  • apa
  • harvard1
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Output format
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