Influence of nozzle asymmetry on supersonic jets

Wlezien, R. W.; Kibens, Valdis

doi:10.2514/3.9846

Cited by 98 publications

(38 citation statements)

References 2 publications

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“…In recent years, several researchers have manipulated the internal contour of jet nozzles cleverly for thrust vectoring, enhanced mixing, and noise reduction. In the published literature such nozzles have been referred to by various names as &&asymmetric'' [40,46,119,140], &&scarfed'' [141], and &&bevelled'' [99,100,102]. Further, rectangular nozzles with non-uniform exits are currently used on advanced military aircraft because of their unique stealth and thrust-vectoring capabilities.…”

Section: Screech From Nozzles Of Nonuniform Exit Geometrymentioning

confidence: 99%

Supersonic Jet Screech: Half-Century From Powell to the Present

Raman

1999

Journal of Sound and Vibration

259

123

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Section: Screech From Nozzles Of Nonuniform Exit Geometrymentioning

confidence: 99%

Supersonic Jet Screech: Half-Century From Powell to the Present

Raman

1999

Journal of Sound and Vibration

259

123

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“…The use of long axial slots inside the nozzle wall as screechsuppressing device was initially proposed by Norum [29] and further investigated by Wlezien and Kibens [30] and Krothapalli et al [31]. These studies report a strong screech attenuation, but their slots are bound to damage the BBSAN component as well due to their large depth.…”

Section: Introductionmentioning

confidence: 99%

Broadband Shock-Associated Noise in Screeching and Non-Screeching Underexpanded Supersonic Jets

2013

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The effect of screech tones on the broadband shock-associated noise of underexpanded jets is investigated experimentally. Screech is removed by means of a notched nozzle, and the properties of the broadband shockassociated noise in the screech-free configuration are compared to that in a screeching flow. It is first demonstrated that the suppressing technique used is nonintrusive in that it does not alter the shock-cell structure of the jet plume. It is then shown that screech has an effect on the aerodynamics of the jet, which induces changes in the broadband shockassociated noise. Indeed, screech accelerates the damping of the shock-cell pattern, leading to an attenuation of the broadband shock-associated noise and a shifting of this noise component to higher frequencies. Moreover, a tuning between the peak frequency of the broadband shock-associated noise and the screech frequency is observed. It is also deduced from the directivity of the broadband shock-associated noise in the far field that the convective velocity in the shear layer is modified in the presence of screech tones.

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“…& Kibens (1988) tested various non axisymmetric supersonic convergent nozzles in a fu lly expanded Mach number range of up to 1.6. They were thus able to produce multiple sources of fine-'scale turbulence and reduce the strain rates in the jet near field.…”

Section: Multistep Jets Schad Ow Et Al (1990) Describe a Circular Nozzlementioning

confidence: 99%