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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.

Place, publisher, year, edition, pages
2006. Vol. 44, no 5, 939-947 p.
Keyword [en]
Mach number, Mass flow, Outflow boundary, Subsonic inflow
National Category
Vehicle Engineering
Identifiers
URN: urn:nbn:se:kth:diva-6291DOI: 10.2514/1.15591ISI: 000237492000002OAI: oai:DiVA.org:kth-6291DiVA: diva2:10967
Note
Uppdaterad från manuskipt till artikel: 20100902 QC 20100902Available from: 2006-10-25 Created: 2006-10-25 Last updated: 2017-12-14Bibliographically approved
In thesis
1. Vortex generator modeling and its application to optimal control of airflow in inlet
Open this publication in new window or tab >>Vortex generator modeling and its application to optimal control of airflow in inlet
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
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:nbn:se:kth:diva-4159 (URN)91-7178-456-X (ISBN)
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

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