Open AccessJournal Article
Experimental Investigation of Mach Reflection in a Shock Tube
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This article is published in Soviet physics. Technical physics.The article was published on 1970-11-01 and is currently open access. It has received 9 citations till now. The article focuses on the topics: Mach reflection & Shock tube.read more
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Experiments on transition of Mach reflexion
L. F. Henderson,A. Lozzi +1 more
TL;DR: In this paper, the transition between regular and Mach reflexion has been investigated and it is shown that the criterion often used to calculate the transition condition is wrong in every case that they have investigated, and they propose an alternative criterion which has the property that the system remains always in mechanical equilibrium during transition.
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Unsteady interactions of shock waves
TL;DR: In this paper, the shape of diffracting waves is calculated by modifying Whitham's theory for the calculation of the shape and the flow pattern of diffracted waves in gases.
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Domains and boundaries of non-stationary oblique shock-wave reflexions. 2. Monatomic gas
Gabi Ben-Dor,I. I. Glass +1 more
TL;DR: In this paper, it is shown analytically and experimentally that in nonstationary flows six domains exist in the (Ms, θw) plane where regular reflexion (RR), single-Mach reflexions (SMR), complex-Mach Reflexions (CMR), and double-Mach Receptions (DMR) can occur.
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Shock waves at a fast-slow gas interface
TL;DR: In this article, the results of experiments on plane shock waves refracting at air/SF6 and He/CO2 interfaces were presented, based on a generalization of the von Neumann (1943) classification of shocks into two classes called weak and strong.
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Further experiments on transition to Mach reflexion
L. F. Henderson,A. Lozzi +1 more
TL;DR: In this paper, the authors reported the results of experiments on shock reflexion in a wind tunnel and a shock tube and further results are presented here, showing that transition to Mach reflexion takes place continuously at the shock wave incidence angle ω 0 corresponding to the normal shock point ω0 = ωN, unless the downstream boundaries form a throat.