Effect of boundary layer on Mach reflection over a wedge surface |
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Authors: | T Adachi A Sakurai S Kobayashi |
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Institution: | (1) Department of Mechanical Engineering, Saitama Institute of Technology, Saitama 369–0293, Japan , JP;(2) Department of Mathematical Sciences, Tokyo Denki University, Tokyo 101–0054, Japan , JP |
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Abstract: | Abstract. In this paper, we consider the phenomenon of unsteady Mach reflection generated by a plane shock wave advancing over a straight
wedge surface, with particular attention to the deviation of the flow field from the self-similar nature. We examine the observed
change in angle between incident and reflected shocks, which is in contrast to the fact that the angle should remain constant
with time in a self-similar flow. The effect of the boundary layer behind the advancing shock wave over the surface of the
wedge is considered to cause this, and boundary layer theory is utilized to estimate the thickness of the layer. It is found
that the thickness increases as to the time t compared with t by the overall expansion in the self-similar flow. Assuming that the thicker boundary layer is effectively equivalent to
a change in wedge angle, the effect of the boundary layer on the flow field should be less in later stages with larger t values in accordance with the observation above.
Received 6 March 2000 / Accepted 23 April 2001 |
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Keywords: | :Mach reflection Non self-similar nature Boundary layer |
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