Abstract
A supersonic compressible flow over a 60° swept delta wing with a sharp leading edge undergoing pitching oscillations is computationally studied. Numerical simulations are performed by the finite volume method with the use of the k−ω turbulence model for various Mach numbers and angles of attack. Variations of flow patterns in a crossflow plane, hysteresis loops associated with the vortex core location, and vortex breakdown positions during a pitching cycle are investigated. Trends for various Mach numbers, mean angles of attack, pitching amplitudes, and pitching frequencies are illustrated.
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Original Russian Text © M. Hadidoolabi, H. Ansarian.
Translated from Prikladnaya Mekhanika i Tekhnicheskaya Fizika, Vol. 58, No. 3, pp. 19–29, May–June, 2017.
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Hadidoolabi, M., Ansarian, H. Numerical analysis of the flow pattern and vortex breakdown over a pitching delta wing at supersonic speeds. J Appl Mech Tech Phy 58, 392–401 (2017). https://doi.org/10.1134/S0021894417030038
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DOI: https://doi.org/10.1134/S0021894417030038