Author/Authors :
Mohsen, A.M. Department of Air-conditioning and Refrigeration Techniques Engineering - University of Warith Al-Anbiyaa, Karbalaa, Iraq , Yusoff, M.Z. Centre of Advanced Computational Engineering - College of Engineering - Universiti Tenaga Nasional, Selangor, Darul Ehsan, Malaysia , Sultan Aljibori, Hakim S. Department of Air-conditioning and Refrigeration Techniques Engineering - University of Warith Al-Anbiyaa, Karbalaa, Iraq , Al-Falahi, A. Sheridan College - Davis Campus, Brampton, Canada , Kadhum, Abdul Amir H. University of Al-Ameed, Karbalaa, Iraq
Abstract :
In the current research, an axisymmetric model is developed to study high-speed unsteady flow in the test section of a
7 meter-long shock tunnel. The computational calculations of the shock tunnel are conducted using the Fluent CFD solver. The
Finite Volume Method (FVM) is used to discretize the governing equations of mass, momentum, and energy. The accuracy of the
numerical model is investigated with first-order upwind, second-order upwind, and third-order MUSCL schemes. Adaptive mesh
refinement is implemented to resolve the shock wave and contact surface regions accurately. The numerical results are compared
with theoretical calculations and experimental data from experimental tests and the comparison shows good agreement.
Different test gases of Helium, Air and CO2, are utilized in the current study. The results show that steady test conditions are
maintained for a longer test time by adjusting the pressure ratio and gas combination across the diaphragm. The highest shock
wave speed and strength are achieved for a gas combination of Helium-CO2, but a longer test duration is observed when using Air
as the test gas.
Keywords :
Shock tunnel , Supersonic flow , Shock wave , CFD , Mach number
