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Please use this identifier to cite or link to this item: http://bura.brunel.ac.uk/handle/2438/6419

Title: Active flow control systems architectures for civil transport aircraft
Authors: Jabbal, M
Liddle, SC
Crowther, WJ
Keywords: Synthetic-jet actuator
Vortex generators
Boundary-layer
Simulation framework
Gas-turbine
Design
Optimization
Publication Date: 2010
Publisher: American Institute of Aeronautics and Astronautics
Citation: Journal of Aircraft 47(6): 1966 - 1981, Nov 2010
Abstract: This paper considers the effect of choice of actuator technology and associated power systems architecture on the mass cost and power consumption of implementing active flow control systems on civil transport aircraft. The research method is based on the use of a mass model that includes a mass due to systems hardware and a mass due to the system energy usage. An Airbus A320 aircraft wing is used as a case-study application. The mass model parameters are based on first-principle physical analysis of electric and pneumatic power systems combined with empirical data on system hardware from existing equipment suppliers. Flow control methods include direct fluidic, electromechanical-fluidic, and electrofluidic actuator technologies. The mass cost of electrical power distribution is shown to be considerably less than that for pneumatic systems; however, this advantage is reduced by the requirement for relatively heavy electrical power management and conversion systems. A tradeoff exists between system power efficiency and the system hardware mass required to achieve this efficiency. For short-duration operation the flow control solution is driven toward lighter but less power-efficient systems, whereas for long-duration operation there is benefit in considering heavier but more efficient systems. It is estimated that a practical electromechanical-fluidic system for flow separation control may have a mass up to 40% of the slat mass for a leading-edge application and 5% of flap mass for a trailing-edge application.
Description: Copyright @ 2010 American Institute of Aeronautics and Astronautics
Sponsorship: This work is funded by the Sixth European Union Framework Programme as part of the AVERT project (Contract No. AST5-CT-2006-030914)
URI: http://www1.aiaa.org/content.cfm?pageid=406&gTable=jaPaper&gid=52842
http://bura.brunel.ac.uk/handle/2438/6419
DOI: http://dx.doi.org/10.2514/1.C000237
ISSN: 0021-8669
Appears in Collections:School of Engineering and Design Research papers
Publications
Mechanical and Aerospace Engineering

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