Calculations of axisymmetric jet leaving a nozzle at jet pressure lower than pressure in medium

Ashratov, E. A.

doi:10.1007/bf01016287

Cited by 8 publications

(3 citation statements)

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“…When p e < p a , which is an overexpanded state, two oblique shock waves are formed at the lips of the nozzle. The interaction of these oblique shock waves along the jet axis, results in either a regular reflection or a Mach reflection, depending on the level of static pressure ratio (p e /p a ) at the nozzle exit (90)(91)(92)(93)(94) . For an highly overexpanded nozzle free jet flow as in the present case with p e /p a = 0•511, the interaction of these oblique shock waves along the jet axis will be of Mach reflection.…”

Section: Flow Structurementioning

confidence: 99%

Triangular tabs for supersonic jet mixing enhancement

Rathakrishnan

2014

Aeronaut. j. (1968)

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The mixing promoting capability of right-angled triangular tab with sharp and truncated vertex has been investigated by placing two identical tabs at the exit of a Mach 2 axi-symmetric nozzle. The mixing promoting efficiency of these tabs have been quantified in the presence of adverse and marginally favourable pressure gradients at the nozzle exit. It was found that, at all levels of expansion of the present study though the core length reduction caused by both the tabs are appreciable, but the mixing caused by the truncated tab is superior. The mixing promoting efficiency of the truncated tab is found to increase with increase of nozzle pressure ratio (that is, decrease of adverse pressure gradient). For all the nozzle pressure ratios of the present study, the core length reduction caused by the truncated vertex tab is more than that of sharp vertex tab. As high as 84% reduction in core length is achieved with truncated vertex right-angled triangular tabs at moderately overexpanded level, corresponding to expansion level p e /p a = 0·90. The corresponding core length reduction for right-angled triangular tabs with sharp vertex and rectangular tabs are 65% and 31%, respectively. The present results clearly show that the mixing promoting capability of the triangular tab is best than that of rectangular tabs at identical blockage and flow conditions.

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Section: Flow Structurementioning

confidence: 99%

Triangular tabs for supersonic jet mixing enhancement

Rathakrishnan

2014

Aeronaut. j. (1968)

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“…(9) and (10) while H 3a and H 4a can be found from Eqs. (5) and (6) by integrations. The correct value of Y 0 would finally satisfy Eq.…”

Section: Two-dimensional Flowmentioning

confidence: 99%

“…It is expected that the occurrence of the Mach reflection and the subsequent interaction between the streams should be such that an equivalent "choking" condition prevails for the downstream central core flow. Indeed, this type of consideration has been adopted for the study of supersonic ejector systems 4 and for the calculations of Mach disk for overexpanded 5 and under-expanded axisymmetric nozzle flows. 6 " 8 In all these later calculations, the slower central core flow was approximated by a simple one-dimensional analysis so that the "choking" condition can be interpreted as "sonic flow at a section of minimum area."…”

Section: Introductionmentioning

confidence: 99%

Mach Reflection Associated with Over-Expanded Nozzle Free Jet Flows

Chow

Chang

1975

AIAA Journal

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The occurrence of Mach reflection within the over-expanded nozzle free jet flow has been examined. A flow model emphasizing the interaction between the outer and central core streams has been developed to deal with flow situations where detailed inviscid calculations of the flowfield with Mach reflection are not possible. The results obtained show reasonably good agreement with the available experimental data. This method has also produced comparable results where detailed calculations of the flowfield are possible.Nomenclature a, b, c = coefficient defined in text, Eq. (11) Y e , R e = nozzle height or radius at exit R 0 = radius of Mach disk R = radius RS = reflected shock H _ = height X, Y, Y -coordinates *o> y 0 = location and height of two-dimensional Mach stem height P = pressure M = nozzle Mach number MS = Mach shock V m = maximum flow velocity V = velocity a = wave angle of shock a = Mach angle y = ratio of specific heats d = deflection angle of shock 6 = streamline angle Subscripts si = sonic limit a = ambient or asymptotic state o -stagnation condition 1 = nozzle flow condition 2 = state behind incident shock 3 = state behind reflected shock at triple point 4 = state behind Mach shock at triple point b = jet boundary r -reflected shock w3 = normal reflected shock at triple point n4 = normal Mach shock at triple point rl = regular reflection limit MS = Mach shock T = triple point 3a= fluid states at asymptotic condition above slipline 4a= fluid states at asymptotic condition below slipline 2 T , 3 r , 4 r = states behind incident, reflected, and Mach shock at triple point (axisymmetry flow only)

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Calculation of the irregular interaction of shock waves

Belotserkovets¹,

Тимошенко²

1993

J Appl Mech Tech Phys

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Calculations of axisymmetric jet leaving a nozzle at jet pressure lower than pressure in medium

Cited by 8 publications

References 0 publications

Triangular tabs for supersonic jet mixing enhancement

Triangular tabs for supersonic jet mixing enhancement

Mach Reflection Associated with Over-Expanded Nozzle Free Jet Flows

Calculation of the irregular interaction of shock waves

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