Investigation of Transient Shock Wave in Supersonic Wind Tunnel

Behnam Ghadimi; Mojtaba Dehghan Manshadi; Mehrdad Bazazzadeh

doi:10.4028/www.scientific.net/AMM.232.228

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HomeApplied Mechanics and MaterialsApplied Mechanics and Materials Vol. 232Investigation of Transient Shock Wave in...

Investigation of Transient Shock Wave in Supersonic Wind Tunnel

Abstract:

Wind tunnels are the experimental apparatuses which provide an airstream flowing under controlled conditions so that interesting items in aerospace engineering such as pressure and velocity can be tested. In this work, Shock wave passes through the intermittent blow-down wind tunnel at Mach=2,3,4 has been investigated. The shape of the nozzle contour for a given Mach number was determined using the method of characteristics. For this purpose MATLAB code was developed and this code was verified with Osher’s and AUSM methods, FORTRAN code and FLUENT software was used for these two methods, respectively. Dimensions of different parts of wind tunnel are determined and minimum pressure ratio for the starting condition has been founded using FLUENT software. Good agreement was considered compared with the data from eleven tunnels over their range of Mach number.

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Periodical:

Applied Mechanics and Materials (Volume 232)

Pages:

228-233

DOI:

https://doi.org/10.4028/www.scientific.net/AMM.232.228

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Online since:

November 2012

Authors:

Behnam Ghadimi, Mojtaba Dehghan Manshadi, Mehrdad Bazazzadeh

Keywords:

AUSM Method, Method of Characteristics, Osher’s Method, Supersonic Wind Tunnel

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References

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