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Vortex generator modeling and its application to optimal control of airflow in inlet
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
2006 (English)Doctoral thesis, comprehensive summary (Other scientific)
Abstract [en]

This dissertation deals with the development of the vortex generator model and its use for the optimization study of vortex generator flow control in high-offset-ed inlets. In the first part, the overview of use of vortex generators and their mechanism is outlined. Both the application form the existing aircraft as well as laboratory studies are reviewed. The second part contains four papers. The first paper deals with the development, verification and validation of the vortex generator model in Navier-Stokes code. Although primarily meant to be used in inlets, the validation of the model was carried out in case of high-lift system by comparing pressure coefficient to the experimental data. Second paper deals with development of the inflow and outflow mass flow boundary conditions for Navier-Stokes codes. Newly designed mass flow boundary conditions were compared to existing mass flow boundary conditions. Special attention was paid to flows under condition of choking. Third paper deals with the Design of Experiment optimization study of the vortex generator flow control in the RAE M2129 inlet with two sets of five geometrical parameters. The aim is to reduce the inlet flow distortion and increase pressure recovery. The parameters of optimal vortex generator setup were then used to design a vortex generator flow control in more realistic inlet for a UAV. Fourth paper deals with testing of vortex generator flow control in the UAV inlet under different flight conditions. In order to be able to find appropriate parameters of flow in inlet, entire UAV with prescribed value of the mass flow was calculated. It was found that the proposed vortex generator installation malfunctioned when at conditions corresponding to the high altitude flight conditions. A new configuration with double number of vortex generators was then tested and at proven being stable. Triangular vortex generators were tested also.

Place, publisher, year, edition, pages
Stockholm: KTH , 2006. , 68 p.
Series
Trita-AVE, ISSN 1651-7660 ; 2006:66
Keyword [en]
vortex generator, vortex generator model, flow control, design and optimization, DOE, CFD, UAV, inlet, S-duct, pressure distortion, pressure recovery
National Category
Vehicle Engineering
Identifiers
URN: urn:nbn:se:kth:diva-4159ISBN: 91-7178-456-X (print)OAI: oai:DiVA.org:kth-4159DiVA: diva2:10970
Public defence
2006-11-06, Sal F3, KTH, Lindstedtsvägen 26, Stockholm, 10:15
Opponent
Supervisors
Note
QC 20100902Available from: 2006-10-25 Created: 2006-10-25 Last updated: 2010-09-02Bibliographically approved
List of papers
1. Vortex-generator model and its application to flow control
Open this publication in new window or tab >>Vortex-generator model and its application to flow control
2005 (English)In: Journal of Aircraft, ISSN 0021-8669, Vol. 42, no 6, 1486-1491 p.Article in journal (Refereed) Published
Abstract [en]

A new vortex-generator model is introduced, the jBAY model, which provides an efficient method for computational-fluid-dynamics (CFD) simulation of flow systems with vortex-generator arrays. The jBAY model is based on the lifting force theory of Bender, Anderson, and Yagle (Bender, E. E., Anderson, B. H., and Yagle, P. J., "Vortex Generator Modelling for Navier-Stokes Codes," American Society of Mechanical Engineers, FEDSM 996919, New York, July 1999) but uses a novel technique for defining the model control points. This greatly simplifies usage of the model as well as improving its performance and accuracy. The jBAY model is described in the context of its implementation in the CFD code Edge, an unstructured Reynolds-averaged Navier-Stokes solver. Results are presented for a single vortex generator on a flat plate and two flow control cases: an S-duct air intake and a high-lift wing configuration. The model is shown to give good agreement with both experimental results and with CFD computations where the vortex generator is fully gridded. It is demonstrated that the jBAY model is simple to apply and efficiently captures the effect of vortex generator arrays for both internal and external flows.

Keyword
Flat plates, Generator arrays, Vortex-generator model, Wing configuration
National Category
Vehicle Engineering
Identifiers
urn:nbn:se:kth:diva-6290 (URN)10.2514/1.12220 (DOI)000233846200013 ()
Note
Uppdaterad från manuskript till artikel: 20100902 QC 20100902Available from: 2006-10-25 Created: 2006-10-25 Last updated: 2010-12-06Bibliographically approved
2. Mass flow boundary conditions for subsonic inflow and outflow boundary
Open this publication in new window or tab >>Mass flow boundary conditions for subsonic inflow and outflow boundary
2006 (English)In: AIAA Journal, ISSN 0001-1452, E-ISSN 1533-385X, Vol. 44, no 5, 939-947 p.Article in journal (Refereed) Published
Abstract [en]

The development and verification of an inflow and outflow mass flow boundary condition are described. In addition, an outflow Mach number boundary condition was implemented and tested. The main motivation behind the development of a mass flow boundary condition is a need to bridge the gap between the requirement of direct setting of mass flow as one of the most important parameters, and the difficulty of indirect control of mass flow using static pressure outflow and total states inflow boundary conditions. The mass flow and Mach number boundary conditions were verified in low-speed flow through a two-dimensional channel with constant area and in high-speed flow through the Royal Airforce Establishment M2129 S-duct with large separation. Special attention was paid to the behavior of the mass flow boundary conditions in choked flow.

Keyword
Mach number, Mass flow, Outflow boundary, Subsonic inflow
National Category
Vehicle Engineering
Identifiers
urn:nbn:se:kth:diva-6291 (URN)10.2514/1.15591 (DOI)000237492000002 ()
Note
Uppdaterad från manuskipt till artikel: 20100902 QC 20100902Available from: 2006-10-25 Created: 2006-10-25 Last updated: 2010-12-06Bibliographically approved
3. Developement and application in design strategy for design of vortex generator flow control in inlets
Open this publication in new window or tab >>Developement and application in design strategy for design of vortex generator flow control in inlets
2006 (English)In: 44th AIAA Aerospace Sciences Meeting and Exhibit9 - 12 January 2006, Reno, Nevada, 2006, 1-14 p.Conference paper, Published paper (Refereed)
Abstract [en]

This article summarizes the results of an optimization study of a micro-vortex generatorflow control in an inlet. Five parametric optimization was carried out using the classicalDesign of Experiment DOE method. Two main objectives were in focus. First, to developthe methodology and skills necessary to conduct a DOE optimization study in relativelynew area of the flow control. Second, to develop the procedures which would be used asa lead during design of flow control in inlets. New information about the behavior of thechannel with flow control were obtained during tests and analyzed. Several interestingconfigurations were located. The parameters of optimal settings were then used to set upthe vortex generator installation in a generic inlet.

National Category
Vehicle Engineering
Identifiers
urn:nbn:se:kth:diva-6292 (URN)
Note
Uppdaterad från manuskript till konferensbidrag: 20100902 QC 20100902Available from: 2006-10-25 Created: 2006-10-25 Last updated: 2010-09-02Bibliographically approved
4. Evaluation of the vortex generator flow control in the FOI-EIC-01 inlet at different flight conditions
Open this publication in new window or tab >>Evaluation of the vortex generator flow control in the FOI-EIC-01 inlet at different flight conditions
2007 (English)In: Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference, 2007, 687-701 p.Conference paper, Published paper (Refereed)
Abstract [en]

The main goal of this work is to test the vortex generator flow control in the FOI-EIC-01 inlet at different flight conditions. The study has two phases. In the first, the entire flow around the UAV with inlet was calculated. Since it is not realistic to run RANS calculations of such a complicated configuration at a large number of flow conditions, the flow around the airframe-propulsion unit system was calculated as inviscid. The data on the boundaries of the inlet are collected and used in the second phase during tests of flow control.

Keyword
Airframes, Flow control, Propulsion, Unmanned aerial vehicles (UAV)
National Category
Vehicle Engineering
Identifiers
urn:nbn:se:kth:diva-6293 (URN)978-156347903-8 (ISBN)
Conference
43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference; Cincinnati, OH; 8 July 2007 through 11 July 2007
Note
QC 20100902Available from: 2006-10-25 Created: 2006-10-25 Last updated: 2010-09-02Bibliographically approved

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Citation style
  • apa
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Output format
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