Experimental and numerical simulation to study the two-dimensional effects due to area contraction near the diaphragm of a shock tube

Al Falahi Amir, Mohd Zamri Yusoff, N. H. Shuaib

Research output: Contribution to journalArticle

Abstract

The aim of this paper is to develop a numerical formulation and an experimental procedure to investigate the effects of area change on flow conditions in shock tube. Two dimensional time accurate Euler solver for shock tube applications was developed to simulate the flow process inside the shock tube. The solver was developed based on the dimensions of a newly built short-duration high speed flow test facility at Universiti Tenaga Nasional "UNITEN" in Malaysia. The facility has been designed, built, and commissioned for different values of diaphragm pressure ratios P 4/P 1 in order to get wide range of Mach number. A bush with diameter less than tube diameter is used to facilitate the rupture process. In the actual experiment, the effective area of the diaphragm (throat) opening at rupture will be some what smaller than the bush opening area. There will be also a dead flow region (recirculating flow) downstream of the bush. The exact location of the reattachment point will be highly dependent on the flow speed. In the present work, since the two parameters are not known, the effective throat area and the wedge angle were calibrated and the values which give the closest agreement between experimental data and CFD simulation results were used. Experimental tests for different operating conditions have been conducted. High precision pressure transducers were used to get the pressure history which represents the shock wave strength P 2/P 1. The agreements obtained between CFD results and experimental measurements have been reasonable.

Original languageEnglish
Pages (from-to)1427-1441
Number of pages15
JournalWorld Academy of Science, Engineering and Technology
Volume38
Publication statusPublished - 01 Feb 2009

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Shock tubes
Diaphragms
Computer simulation
Computational fluid dynamics
Pressure transducers
Test facilities
Shock waves
Mach number
Experiments

All Science Journal Classification (ASJC) codes

  • Engineering(all)

Cite this

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