UFR 4-19 Evaluation: Difference between revisions
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h<sub>1</sub> = 2.822, h<sub>2</sub> = 4.611, h<sub>3</sub> = 6.340 and h<sub>4</sub> = 7.493. | h<sub>1</sub> = 2.822, h<sub>2</sub> = 4.611, h<sub>3</sub> = 6.340 and h<sub>4</sub> = 7.493. | ||
Figure 9 | <div id="figure9"></div> | ||
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|[[Image:UFR4-19_Fig9.png|650px]] | |||
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|align="center"|'''Figure 9:''' Shock-waves positions and experimental measurements | |||
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Revision as of 12:23, 12 April 2016
Converging-diverging transonic diffuser
Confined flows
Underlying Flow Regime 4-19
Evaluation
Comparison of CFD Calculations with Experiments
For both "weak" and "strong" Mach number cases,for comparison with the calculations, experimental data for four measurements stations after the shock-wave (h1, h2, h3, h4) are selected for the longitudinal velocity as well as pressure distributions along the bottom and the top wall of the diffuser. A representative figure of the shock-wave positions and the measurement stations is shown in fig.9.The x-location of the axial measurement stations are non-dimensionalized with the diffuser throat height,resulting in the following four stations: h1 = 2.822, h2 = 4.611, h3 = 6.340 and h4 = 7.493.
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| Figure 9: Shock-waves positions and experimental measurements |
Contributed by: Z. Vlahostergios, K. Yakinthos — Aristotle University of Thessaloniki, Greece
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