Numerical Investigation of Sweep Angle Effect on the Supersonic Flows through Corners
Publication: Journal of Aerospace Engineering
Volume 30, Issue 4
Abstract
This research intends to characterize numerically the impact of sweep angle on the supersonic sharp corner flows. For this purpose, the effect of sweep angle on the variations of flow parameters such as shear stress, temperature, and pressure on the corner surface and also on the shock structure is examined. To ensure the accuracy of current numerical model, validation is performed with previous researches and reasonable agreements are observed. Results indicate that the inclusion of sweep angle has a significant effect on the Mach reflection strength and thus on the flow parameters’ variations on the corner surface. It is found that the role of sweep angle in changing the flow parameters’ variations in the zones near the trailing edge is of less significance than those that are close to the leading edge. It is shown that the inclusion of sweep angle has a little effect on the separation zone size although it tends to increase slightly the separation region length along the wing span at the trailing edge. Results demonstrate that the increase in sweep angle causes the shock structure and thus the Mach stem to become closer to the wing geometry. It is also seen that an increase in sweep angle leads to an increase in the Mach stem length.
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Published In
Journal of Aerospace Engineering
Volume 30 • Issue 4 • July 2017
Copyright
©2017 American Society of Civil Engineers.
History
Received: Dec 31, 2014
Accepted: Oct 12, 2016
Published ahead of print: Jan 29, 2017
Published online: Jan 30, 2017
Discussion open until: Jun 30, 2017
Published in print: Jul 1, 2017
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