The perturbed region behind a diffracting shock wave

Skews, B. W.

doi:10.1017/s0022112067001132

Cited by 131 publications

(61 citation statements)

References 4 publications

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“…It can be noted that the occurrence of the lambda shock is not affected by the presence of the coflow shear layer. From Skews [6], in a quiescent gas, multiple lambda shocks are observed on the shear layer for Mach numbers 1.4 to 1.5. In the present flow configuration a single lambda shock occurs, in agreement with previous findings.…”

Section: Ramp Geometrymentioning

confidence: 99%

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Shock wave diffraction in the presence of a supersonic co-flow jet

Gnani

Zare‐Behtash

et al. 2016

Shock Waves

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The interaction between a diffracting shock wave and a uniform jet is a case that so far has only been partially investigated. This interaction is extremely important for the control of noise generation and improvement of combustor performance. To fill this knowledge gap, three geometries of the diffracting corner, namely a straight ramp, a serrated ramp, and a rounded corner, have been tested experimentally to study the interaction of shock diffraction with a supersonic co-flow jet at incident Mach numbers of 1.31 and 1.59, with Reynolds numbers of 1.08 × 10 6 and 1.68 × 10 6 , respectively. Schlieren photography was employed to analyse the evolution of the flow phenomena. The aim is to provide a qualitative understanding of the interaction between the diffracting shock wave and the uniform jet relevant to future high-speed transport. The results show that the flow field evolves more rapidly and develops stronger structures for a higher shock Mach number. The diffraction around a rounded splitter develops a periodical vortical structure which continues after the disturbance introduced by the passage of the shock wave is removed.Keywords Shock wave diffraction · Vortex · Schlieren · Unsteadiness 1 Nomenclature ASCurved acoustic wave CS Contact surface CF SL Co-flow shear layer

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Section: Ramp Geometrymentioning

confidence: 99%

“…The flow features that characterise the shock wave diffraction without co-flow have been analysed with incident shock Mach numbers in the range of 1.0 to 5.0 [6]. However, the complexity of the flow scenario and the small time scales have made the capture and analysis of the processes quite challenging.…”

Section: Introductionmentioning

confidence: 99%

Shock wave diffraction in the presence of a supersonic co-flow jet

Gnani

Zare‐Behtash

et al. 2016

Shock Waves

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“…In an experimental study, Skews [25] obtained schlieren images that identified the features of the flow. An unsteady expansion fan is generated at the corner.…”

Section: Jet Formation Time Scalesmentioning

confidence: 99%

Exhaust of Underexpanded Jets from Finite Reservoirs

Orescanin

Prisco

Austin

2010

Journal of Propulsion and Power

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The response of an underexpanded jet to a depleting finite reservoir is examined with experiments and simulations. An open-ended shock-tube facility with a variable reservoir length is used to obtain images of nitrogen-and heliumjet structures at successive instances during the blowdown from initial pressure ratios of up to 250. The reservoir and ambient pressures are simultaneously measured to obtain the instantaneous pressure ratio. We estimate the time scales for jet formation and reservoir depletion as a function of the specific heat ratio of the gas and the initial pressure ratio. The jet structure formation time scale is found to become approximately independent of the pressure ratio for ratios greater than 50. In the present work, no evidence of time dependence in the Mach disk shock location is observed for rates of pressure decrease associated with isentropic blowdown of a finite reservoir while the pressure ratio is greater than 15. The shock location in the finite-reservoir jet can be calculated from an existing empirical fit to infinite-reservoir jet data evaluated at the instantaneous reservoir pressure. For pressure ratios below 15, however, the present data deviate from a compilation of data for infinite-reservoir jets. A new fit is obtained to data in the lower-pressure regime. The self-similarity of the jet structure is quantified, and departure from similarity is noted to begin at pressure ratios lower than about 15, approximately the same ratio that limits existing empirical fits.

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“…Within this region the existence of various disturbances can be postulated or have I been identified experimentally (e.g. Skews, 1967aSkews, , 1967bBazhenova et al, 1971). The initial expansion is a truly steady region, turning the fluid to the appropriate separation angle for the vortex sheet at A.…”

Section: Strong Shock Diffractionmentioning

confidence: 99%

Proceedings of the International Symposium on Shock Tubes and Waves (13th), Niagara Falls, July 6-9, 1981.

Treanor¹,

Hall²

1981

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The perturbed region behind a diffracting shock wave

Cited by 131 publications

References 4 publications

Shock wave diffraction in the presence of a supersonic co-flow jet

Shock wave diffraction in the presence of a supersonic co-flow jet

Exhaust of Underexpanded Jets from Finite Reservoirs

Proceedings of the International Symposium on Shock Tubes and Waves (13th), Niagara Falls, July 6-9, 1981.

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