01-10-2014, 09:51 AM
Abstracts: The sizing and efficiency of an aircraft is largely determined by the performance of its high-lift system. Subsonic civil transports most often use deployable multi-element aerofoils to achieve the maximum-lift requirements for landing, as well as the high lift-to-drag ratios for take-off. However, these systems produce very complex flow fields which are not fully understood by the scientific community. In order to compete in today's market place, aircraft manufacturers will have to design better high-lift systems. As part of this effort, computational aerodynamic tools are being used to provide preliminary flowfield information for instrumentation development, and to provide additional insight during the data analysis and interpretation process. Flow computation around a simplified three element high lift configuration without the fuselage and a realistic high lift configuration with fuselage are performed to study flow near wing-fuselage junction and also determine the flow separation with angle of attack.