Abstract
The proposed test-case is the inherently unsteady flow over a 18% thick circular arc aerofoil at 0-deg angle of attack, Mach number 0.76 and Reynolds number 11 × 106, based on the chord length. Shock-induced separation is occurred at the foot of the shock wave, which is extended downstream beyond the trailing edge. Experimental data and numerical results for the time histories of the pressure, the mean velocity components and the mean flow direction on specific positions on the aerofoil’s surface are available in ref. [1].
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References
SEEGMILLER, H.L., MARVIN, J.G. & LEVY, L.L. 1978 “Steady and unsteady transonic flow”. AIAA J., Vol. 16, N°12, pp 1262, 1270.
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© 1998 Friedr. Vieweg & Sohn Verlagsgesellschaft mbH, Braunschweig/Wiesbaden
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Braza, M., Tsangaris, S. (1998). Presentation of the Test-Case TC8 bis. In: Dervieux, A., Braza, M., Dussauge, JP. (eds) Computation and Comparison of Efficient Turbulence Models for Aeronautics — European Research Project ETMA. Notes on Numerical Fluid Mechanics (NNFM), vol 5. Vieweg+Teubner Verlag, Wiesbaden. https://doi.org/10.1007/978-3-322-89859-3_58
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DOI: https://doi.org/10.1007/978-3-322-89859-3_58
Publisher Name: Vieweg+Teubner Verlag, Wiesbaden
Print ISBN: 978-3-322-89861-6
Online ISBN: 978-3-322-89859-3
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