Journal of Flow Visualization and Image Processing

ISSN for PRINT: 1065-3090

For Online Access

Best Paper Award Selection - Editorial Board Site

2005, Volume12

Issue 2

92 pages

DOI: 10.1615/JFlowVisImageProc.v12.i2

Issue price - $154.00

Jr-Ming Miao
Department of Mechatronic, Energy and Aerospace Engineering, Chung Cheng Institute of Technology, National Defense University, Taoyuan, Taiwan 335, R.O.C.

Chun-Chi Li
Department of Mechanical Engineering, Chung Cheng Institute of Technology, National Defense University, Taoyuan, Taiwan 335, R.O.C

Fuh-Lin Lih
School of Defense Science Studies, Chung Cheng Institute of Technology, National Defense University, Taoyuan, Taiwan 335, R.O.C

This study numerically analyzes transient multi-shock flow phenomena in a full-reflection shock tunnel using CFD. Based on the finite volume method, the compressible Navier-Stokes equations are solved with the upwind Roe's scheme and the total variation diminishing (TVD) scheme. To consider the real gas effect, the polynomial correlations of Tannehill and Mugge are applied to modify the equation of state in simulating the hypersonic environment. For either a perfect or viscous flow with the real gas effect, the flow features of the shock train, reflected shock wave/boundary layer interaction in the shock tube, and the Mach reflection configuration in startup process of nozzle flow are clearly observed in this work. The effect of the half-nozzle angle on the startup process of nozzle flow is also explored. The flow establishment time from placing a spherical model in the test section is 8.0 ms, and the effective flow test time is 3.5 ms.

DOI: 10.1615/JFlowVisImageProc.v12.i2.60 Download article, 175-195 pages

Article price - $40.00

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