Summary
The accuracy of an unstructured Navier-Stokes solver in predicting the airflow around the common tailplane airfoil NACA 64A010 at low Reynolds numbers is investigated. Since the performance of this airfoil is strongly affected by the transition of the boundary layer, the calculations using the Spalart-Allmaras, k-ω and k-ω SST models are carried out with specified transition positions on the airfoil’s surface. It turns out, that the Navier-Stokes solver can predict leading edge stall via the appearance of laminar separation bubbles. However, the code is less accurate in predicting the flow around airfoils with deflected rudders, where the onset of boundary layer separation as a result of two consecutive regions of adverse pressure gradients is predicted at too high angles of attack.
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© 2004 Springer-Verlag Berlin Heidelberg
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Grote, A., Kruse, M., Radespiel, R. (2004). Calculation of attached and separated flow for a tailplane airfoil with rudder. In: Breitsamter, C., Laschka, B., Heinemann, HJ., Hilbig, R. (eds) New Results in Numerical and Experimental Fluid Mechanics IV. Notes on Numerical Fluid Mechanics and Multidisciplinary Design, vol 87. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-540-39604-8_7
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DOI: https://doi.org/10.1007/978-3-540-39604-8_7
Publisher Name: Springer, Berlin, Heidelberg
Print ISBN: 978-3-642-53546-8
Online ISBN: 978-3-540-39604-8
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