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Eliminating Flow Separation and Reducing Viscous Drag Through Boundary Layer Analysis and ManipulationAs both computers and flow-analyzing equations have increased in sophistication, Computational Fluid Dynamics (CFD) has evolved into a fixture for advanced aircraft design. While CFD codes have improved in accuracy and efficiency, their ability to encompass viscous effects is lacking in certain areas. For example, current CFD codes cannot accurately predict or correct for the increased drag due to these viscous effects at some flow conditions. However, by analyzing an airfoil's turbulent boundary layer, one can predict not only flow separation via the shape factor parameter, but also viscous drag via the momentum thickness. Various codes have been written which can calculate turbulent boundary layer parameters. The goal of my research is to develop procedures for modifying an airfoil (via its local pressure distribution) to eliminate boundary layer separation and/or to reduce viscous drag. The modifications to the local pressure distribution necessary to achieve these objectives will be determined using a direct-iterative method installed into a turbulent boundary layer analyzer. Furthermore, the modifications should preserve the basic characteristics of the original airfoil.
Document ID
19970003102
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Oser, Matthew D.
(Illinois Univ. Champaign, IL United States)
Date Acquired
August 17, 2013
Publication Date
January 1, 1995
Publication Information
Publication: Langley Aerospace Research Summer Scholars
Volume: Part 2
Subject Category
Fluid Mechanics And Heat Transfer
Accession Number
97N11867
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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