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Modelling of unsteady aerodynamics for aircraft design
Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems. Linköping University, The Institute of Technology.
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 [en]
Aircraft Deisgn, Aerodynamic
National Category
Engineering and Technology
Identifiers
URN: urn:nbn:se:liu:diva-40992Local ID: 54827ISBN: 91-7373-769-0 (print)OAI: oai:DiVA.org:liu-40992DiVA: diva2:261842
Available from: 2009-10-10 Created: 2009-10-10 Last updated: 2013-12-12
List of papers
1. Lift Coefficient Predictions for Delta Wing Under Pitching Motions
Open this publication in new window or tab >>Lift Coefficient Predictions for Delta Wing Under Pitching Motions
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
National Category
Engineering and Technology
Identifiers
urn:nbn:se:liu:diva-40982 (URN)10.2514/6.2002-2969 (DOI)54814 (Local ID)54814 (Archive number)54814 (OAI)
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
2. Modeling of Unsteady Aerodynamic Charactersitics of Delta Wings
Open this publication in new window or tab >>Modeling of Unsteady Aerodynamic Charactersitics of Delta Wings
2002 (English)In: Proceedings 23rd International Congress of Aeronautical Sciences (ICAS), Toronto: ICAS , 2002Conference paper, Published paper (Refereed)
Abstract [en]

An analytic prediction model is presented to estimate aerodynamic coefficient of delta wing undergoing dynamic motions. The model is based on the introduction of a state space variable describing the vortex breakdown. This model will be suitable for modeling of flight dynamics in the preliminary design phase.

Place, publisher, year, edition, pages
Toronto: ICAS, 2002
Keyword
delta wings, unsteady, modeling, preliminary design, aerodynamic coefficient
National Category
Engineering and Technology
Identifiers
urn:nbn:se:liu:diva-40989 (URN)54823 (Local ID)0-9533991-3-3 (ISBN)54823 (Archive number)54823 (OAI)
Conference
23nd Congress of International Council of the Aeronautical Sciences, Toronto, Canda, 2002 (ICAS 2002)
Available from: 2009-10-10 Created: 2009-10-10 Last updated: 2013-12-12
3. Aircraft manoeuvers simulation, steady and unsteady aerodynamic
Open this publication in new window or tab >>Aircraft manoeuvers simulation, steady and unsteady aerodynamic
2003 (English)In: SAE Technical Paper, Montreal, Canada: World Aviation Congress , 2003, 2003-01-3034- p.Conference paper, Published paper (Refereed)
Abstract [en]

The current work present a simple model to integrate non-linear aerodynamic in conceptual design phase, before wind tunnel testing. A presentation of a simple pitch up maneuver based on three different aerodynamic models is simulated. The simulation indicates different behaviors depending on the aerodynamic model, and shows the importance of including unsteady aerodynamic.

Place, publisher, year, edition, pages
Montreal, Canada: World Aviation Congress, 2003
National Category
Engineering and Technology
Identifiers
urn:nbn:se:liu:diva-36426 (URN)10.4271/2003-01-3034 (DOI)31303 (Local ID)31303 (Archive number)31303 (OAI)
Conference
World Aviation Congress, Montreal, Canada. 9-11 September 2003
Available from: 2009-10-10 Created: 2009-10-10 Last updated: 2013-12-12
4. Distributed aircraft analysis using web service technology
Open this publication in new window or tab >>Distributed aircraft analysis using web service technology
2003 (English)In: SAE Technical Paper, 2003, 2003-01-3007- p.Conference paper, Published paper (Refereed)
Abstract [en]

The design modern aircraft requires integration of multidisciplinary models for analysis in early design phase to increase the chances of a successful project. In this paper, a framework for distributed aircraft analysis in the conceptual design including several domains is presented. The framework is based on so-called W eb service standards, allowing integration of distributed models for system simulation and optimization using standardized interfaces. The analysis is controlled by a so-called sequencer which manages the interaction between simulation modules and an XML-based design data repository. This repository includes all design data and an executable process description defining the sequence for execution of the modules.

In the paper, the framework with underlying concepts is described. The approach is further illustrated using the design of an Unmanned Aerial Vehicle as an example. This includes the definition of the simulation modules, the process model and definition and execution of an optimization problem.

National Category
Engineering and Technology
Identifiers
urn:nbn:se:liu:diva-102504 (URN)10.4271/2003-01-3007 (DOI)
Conference
World Aviation Congress. Montreal, Canada. 9-11 September, 2003
Available from: 2013-12-12 Created: 2013-12-12 Last updated: 2013-12-12

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