Al-Falahi, Amir and Yusoff, M. Z. and Yusaf, Talal and Ahmed, Diyar I. (2012) Numerical investigation of flow instability in shock tube due to shock wave-contact surface interactions. International Journal of Numerical Methods for Heat and Fluid Flow, 22 (3). pp. 377-398. ISSN 0961-5539
Purpose - The aim of this paper is to perform a CFD simulation that is able to reveal what is happening for the shock wave generated by high speed flow test facility. The main purpose of this study is to develop deeper understanding of all parameters which affect the shock wave velocity profile and pressure and temperature histories inside the facility
Design/methodology/approach - Two dimensional time accurate Euler solver for shock tube applications was developed to simulate the flow process inside the shock tube. To ensure the ability of the CFD code to capture shocks, rarefaction waves and contact discontinuity and to produce the correct pressure, temperature, density and speed profiles, the code has been validated using two verification approaches. Firstly, the code results have been compared to the Sod’s tube problem (exact solution). Secondly, the code solution is compared with selected experimental measurements for a certain diaphragm pressure ratio.
Findings - Results presented in this paper show that after diaphragm rapture and when the shock did not reflect yet, the flow is symmetry and uniform in y-direction. As the shock wave reflects from the tube end it will move to the left and interact with the discontinuity surface and the flow no longer symmetry. Results also show that two-dimensional modeling of the high speed flow test facility is an effective way to obtain facility performance data. Although this paper focused on UNITEN’s facility, the CFD code is generic and may be applied to other facilities. The present code showed good capability to provide the x-t diagram successfully. From this diagram one can determine the useful duration (for this case it is about 10 ms), which is quite comparable compared to other facilities. It can be concluded, based on the agreement with the analytical results, that the numerical formulation for the inviscid part of the solver is valid.
Originality/value - It is becoming increasingly difficult to ignore the role of short duration high speed flow test facilities. Recent developments in the field of supersonic and hypersonic applications have led to a renewed interest in this kind of test facilities. Recently, researchers have shown an increased interest in high speed flow conditions which can be used to simulate the real conditions encountered by aerospace vehicles. So far, however, there has been little discussion about the characteristics of the flow process inside these test facilities. Furthermore, far too little attention has been paid to discuss the parameters which affect the velocity profile inside these test facility. Consequently, this has heightened the need for a comprehensive and an integral study which is aided by computer capabilities such as CFD technique.
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|Item Type:||Article (Commonwealth Reporting Category C)|
|Item Status:||Live Archive|
|Additional Information:||Permanent restricted access to published version due to publisher copyright policy.|
|Faculty / Department / School:||Historic - Faculty of Engineering and Surveying - Department of Mechanical and Mechatronic Engineering|
|Date Deposited:||03 Feb 2012 06:03|
|Last Modified:||18 Jul 2014 04:32|
|Uncontrolled Keywords:||heat transfer; shock wave; aerospace industry; shock tube; computational fluid dynamics; flow; pressure; shock tunnel; temperature; velocity|
|Fields of Research :||09 Engineering > 0915 Interdisciplinary Engineering > 091501 Computational Fluid Dynamics
09 Engineering > 0913 Mechanical Engineering > 091307 Numerical Modelling and Mechanical Characterisation
09 Engineering > 0915 Interdisciplinary Engineering > 091502 Computational Heat Transfer
|Socio-Economic Objective:||B Economic Development > 85 Energy > 8504 Energy Transformation > 850499 Energy Transformation not elsewhere classified|
|Identification Number or DOI:||doi: 10.1108/09615531211208079|
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