IEEJ Transactions on Sensors and Micromachines
Online ISSN : 1347-5525
Print ISSN : 1341-8939
ISSN-L : 1341-8939
Paper
Study on Correlation between Geometrical Correction and Aerodynamic Performance of Microscale Supersonic Wind Tunnel
Naoki MuraiRyouto YamamotoKouhei RikunoToshiyuki Toriyama
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2018 Volume 138 Issue 4 Pages 145-152

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Abstract

In this paper, flow visualization of the oblique shock waves of a single-crystal-silicon microscale supersonic wind tunnel is described. The microscale supersonic wind tunnel has a convergent - divergent section and a throat area of 1000µm×300µm, and designed for realizing supersonic flow of Mach 2 in microscale domain. The schlieren system with integrated optical microscope was used for visualization of the oblique shock waves generated in the microscale domain. To investigate the effect of nonisentropic flow state on the inclination angle to the shock, a numerical integration of the modified Shapiro's differential equation was applied.

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© 2018 by the Institute of Electrical Engineers of Japan
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