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Direct numerical simulation of flow past a transversely rotating sphere up to a Reynolds number of 300 in compressible flow

Published online by Cambridge University Press:  30 October 2018

T. Nagata Open the ORCID record for T. Nagata [Opens in a new window] ,
T. Nonomura Open the ORCID record for T. Nonomura [Opens in a new window] ,
S. Takahashi ,
Y. Mizuno  and
K. Fukuda
T. Nagata*
Affiliation:
Department of Aerospace Engineering, Tohoku University, 6-6-01, Aramaki, Aoba-ku, Sendai, Miyagi, 980-8579, Japan
T. Nonomura
Affiliation:
Department of Aerospace Engineering, Tohoku University, 6-6-01, Aramaki, Aoba-ku, Sendai, Miyagi, 980-8579, Japan
S. Takahashi
Affiliation:
Department of Prime Mover Engineering, Tokai University, 4-4-1, Kita-kaname, Hiratsuka, Kanagawa, 259-1292, Japan
Y. Mizuno
Affiliation:
Course of Science and Technology, Tokai University, 4-4-1, Kita-kaname, Hiratsuka, Kanagawa, 259-1292, Japan
K. Fukuda
Affiliation:
Department of Aeronautics and Astronautics, Tokai University, 4-4-1, Kita-kaname, Hiratsuka, Kanagawa, 259-1292, Japan
*
†Email address for correspondence: nagata.takayuki@aero.mech.tohoku.ac.jp
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Abstract

In this study, direct numerical simulation of the flow around a rotating sphere at high Mach and low Reynolds numbers is conducted to investigate the effects of rotation rate and Mach number upon aerodynamic force coefficients and wake structures. The simulation is carried out by solving the three-dimensional compressible Navier–Stokes equations. A free-stream Reynolds number (based on the free-stream velocity, density and viscosity coefficient and the diameter of the sphere) is set to be between 100 and 300, the free-stream Mach number is set to be between 0.2 and 2.0, and the dimensionless rotation rate defined by the ratio of the free-stream and surface velocities above the equator is set between 0.0 and 1.0. Thus, we have clarified the following points: (1) as free-stream Mach number increased, the increment of the lift coefficient due to rotation was reduced; (2) under subsonic conditions, the drag coefficient increased with increase of the rotation rate, whereas under supersonic conditions, the increment of the drag coefficient was reduced with increasing Mach number; and (3) the mode of the wake structure becomes low-Reynolds-number-like as the Mach number is increased.

JFM classification

Aerodynamics: Aerodynamics Aerodynamics: High-speed flow Low-Reynolds-number flows: Low-Reynolds-number flows
Type
JFM Papers
Information
Journal of Fluid Mechanics , Volume 857 , 25 December 2018 , pp. 878 - 906
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Copyright
© 2018 Cambridge University Press 

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