Numerical Investigation of Shock Wave Decay Phenomenon in Free Atmosphere

Md. Faisal Kader^1, , M. Monjurul Ehsan², Golam Saklayen¹, KMR Sadi¹ and Md. Lutfor Rahman¹

¹Military Institute of Science and Technology (MIST), Mirpur Cantonment, Dhaka-1216, Bangladesh

²Islamic University of Technology (IUT), The Organization of Islamic Cooperation (OIC), Board Bazar, Gazipur-1704, Bangladesh

Cite this paper:
Md. Faisal Kader, M. Monjurul Ehsan, Golam Saklayen, KMR Sadi and Md. Lutfor Rahman. Numerical Investigation of Shock Wave Decay Phenomenon in Free Atmosphere. American Journal of Mechanical Engineering. 2016; 4(5):200-208. doi: 10.12691/ajme-4-5-5

Abstract

A numerical investigation of shock wave propagation in open atmosphere is presented to observe the shock wave decaying phenomena due to expansion in the free space. By examining different parameters (Pressure, velocity and density) of the upstream and downstream flow of the wave, it is possible to estimate the decaying phenomena of the wave strength. The governing equations described for compressible inviscid flow are discretized by the finite volume method. The three-dimensional Euler equations are solved by shock capturing method. Shock wave of Mach number 1.5 is allowed to flow through a shock tube and at different time intervals (35 μsec, 96 μsec, 121 μsec and 190 μsec), velocity, pressure and density variations along the center line of shock tube are investigated to observe the decay phenomenon across the shock front in open atmosphere.. The results have been compared with the Navier-Stokes Simulation (NS) results to establish the absence of viscous effects in the present flow. Due to absence of the solid boundary of the selected numerical domain in the free space, the fluid flow will act as non-viscous flow. The wave propagation in free space changes its propagation characteristics due to rapid expansion in all directions and at the same time the decay of the wave strength is observed.

Keywords:
shock wave shock tube propagation decay free atmosphere

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References:

[1]	Ribner, H. S. 1953, “Convection of a pattern of vorticity through a shock wave.” NACA TN-2864, 1953.
[2]	Ribner, H. S. 1954, “Shock-turbulence interaction and the generation of noise.” NACA TN-3255, 1954.
[3]	Ribner, H. S. 1969, “Acoustic energy flux from shock-turbulence interaction.” Journal of Fluid Mechanics Vol. 35, 1969, pp. 299-310.
[4]	Kovasznay, L. S. G. 1953, “Turbulence in supersonic flow.” J. Aero. Sci. Vol. 20, pp. 657-682.
[5]	Lighthill, M. J. 1953, “On the energy scattered from the interaction of turbulence with sound or shock wave.” Proc. Camb. Phil. Soc. 49, 531-551.
[6]	Moore, F. K. 1953, “Unsteady oblique interaction of a shock wave with a plane disturbances.” NACA TN-2879, 1953.
[7]	Anyiwo, J. C. & Bushnell, D. M. 1982, “Turbulence amplification in shock-wave boundary-layer interaction.” AIAA J. Vol. 20, 893-899.
[8]	Craig JE, 1977, “Shock waves in open ended ducts with complex geometry.” Ph D Aeronautics, California Institute of Technology, Pasdene CA, USA.
[9]	Onodera H, Takayama K, 1992, “An analysis of shock wave propagation over perforated wall and its discharge coefficient”, Trans Jpn Soc Mech Eng B (in Japanese). 58:1408.
[10]	Takayama K, Sasoh A, Onodera O, Kaneko R, Matsui Y, 1995, “Experimental investigation on tunnel sonic boom”. Shock Waves 5:127(138).
[11]	Batley, G.A., McIntosh, A.C., Brindley, J., Falle, S.A.E.G., 1994, “A numerical study of the vorticity field generated by the baroclinic effect due to the propagation of a planar pressure wave through a cylindrical premixed laminar flame”. J. Fluid Mech. 279, 217-237.
[12]	Gelfand, B.E., Khomik, S.V., Bartenev, A.M., Medvedev, S.P., Groing, H., Olivier, H., 2000, “Detonation and deflagration at the focusing of shockwaves in combustible gaseous mixture” Shock Waves, 10, 197-204.
[13]	Bartenev, A.M., Khomik, S.V., Gelfand, B.E., Gronig, H., Olivier, H., 2000, “Effect of reflection type on detonation initiation at shock-wave focusing.” Shock Waves 10, 205-215.
[14]	Abdellah Hadjadj, Marcello Onofri, 2009, “Nozzle flow separation”. Shock Waves, 19:163-169.
[15]	Trimpi, R.L., Cohen, N.B., 1955, “A theory for predicting the flow of real gases in shock tubes with experimental verification.” Technical Report NACA 3375, National Advisory Committee for Aeronautics.
[16]	Emrich, R.J., Wheeler, D.B., 1958, “Wall effects in shock tube flow” Phys. Fluids 1, 14-23.
[17]	Mirels, H., 1957, “Attenuation in a shock tube due to unsteady-boundary layer action.” Technical Report TN 1333, National Advisory Committee for Aeronautics.
[18]	Roshko, A., 1960, “On flow duration in low-pressure shock tubes.” Phys. Fluids 3(6), 835-842.
[19]	Mirels, H., 1966, “Correlation fomulas for laminar shock tube boundary layer.” Phys. Fluids 9(7), 1265-1272.
[20]	Chen, C.J., Emrich, R.J., 1963, “Ivestigation of the shock-tube boundary layer by a tracer method.”, Phys. Fluids 6(1), 1-9.
[21]	Yanchao Shi, Hong Hao and Zhong-Xian Li, 2007, “Numerical simulation of blast wave interaction with structure columns.”, Shock Waves Journal, Vol. 17: 113-33.
[22]	O. Igra, L. Wang, J. Falcovitz and W. Heilig, 1998, “Shock wave propagation in a branched duct.” Shock Waves Journal, Vol. 8: 375-81.
[23]	Rotman D, 1991, “Shock wave effects on a turbulent flows.” Phys. Fluids A3: 1792-806.
[24]	Jinnah MA, 2005, “Numerical and experimental study of Shock/Turbulent flow interaction.” Doctor Thesis, Tohoku University.