Abstract
Direct numerical simulations of the three-dimensional time-dependent compressible Navier-Stokes equations are performed to investigate leading edge transition flows at realistic Reynolds number with the pressure gradient distributions from real aerofoils. The potential flow solution from an aerofoil calculation is used to setup a leading edge flowfield, which includes the stagnation point and the pressure gradient region downstream of the suction peak. A rectangular computational domain is used to retain the essential flow features with minimal computational cost. Potentially this approach could be a way to predict the lift curve of an arbitrary aerofoil.
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© 2001 Springer Science+Business Media Dordrecht
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Alam, M., Sandham, N.D. (2001). DNS of Transition near the Leading Edge of an Aerofoil. In: Geurts, B.J., Friedrich, R., Métais, O. (eds) Direct and Large-Eddy Simulation IV. ERCOFTAC Series, vol 8. Springer, Dordrecht. https://doi.org/10.1007/978-94-017-1263-7_35
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DOI: https://doi.org/10.1007/978-94-017-1263-7_35
Publisher Name: Springer, Dordrecht
Print ISBN: 978-90-481-5893-5
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