Numerical Investigation of Screech for a 2d Underexpanded Supersonic Rectangular Jet PDF Download
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Author: Timothy J. Rozmajzl
Publisher:
ISBN:
Category :
Languages : en
Pages : 198
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Author: Timothy J. Rozmajzl
Publisher:
ISBN:
Category :
Languages : en
Pages : 198
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Author: Edward J. Rice
Publisher:
ISBN:
Category :
Languages : en
Pages : 16
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Author: Ted A. Manning
Publisher:
ISBN:
Category :
Languages : en
Pages : 408
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Author: Ted A. Manning
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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The noise of supersonic jet flows is due in part to the interaction between jet instability waves and the jet shock-cell structure. If no countermeasures are taken, the emitted shock-cell noise will re-excite certain instability wave modes at the nozzle lip and cause resonant feedback to occur. This feedback resonance, known as supersonic jet screech, causes the jet to flap violently at discrete frequencies and generate very strong, narrow banded tones. Jet screech has been shown to be a source of acoustic fatigue in the tail and nozzle structures of supersonic aircraft. It is important that methods for predicting the screech amplitude be developed. Screech sound generation is one such element. We isolate the interaction of an unsteady shear layer with a single oblique shock. To obtain an overall understanding of the phenomenon with fewest simplifications, we study this problem through the numerical solution of the Navier Stokes equations. We then consider idealizations which allow us to obtain a similar but wider range of results with specially linearized Euler equations. The findings of these r0sults motivate the use of geometric acoustics to describe the screech generation process. The Navier-Stokes and Euler simulations have revealed important details about the interaction process, how the acoustic field results, and why screech is so loud. The mechanism for sound production is found to be fundamentally different and more efficient when the instability waves are the large vortices typical of screech, than when they are small disturbances. Geometrical acoustics can be used to explain the leakage effect at high instability wave amplitude. We conclude that the mechanism for high amplitude screech generation is an unsteady modification to the velocity field by the instability waves that permits the incident shock to refract through the shear layer.
Author: Ganesh Raman
Publisher:
ISBN:
Category :
Languages : en
Pages : 28
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Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781792775833
Category :
Languages : en
Pages : 28
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It is known experimentally that an imperfectly expanded rectangular jet from a thin-lip convergent nozzle emits only a single dominant screech tone. The frequency of the screech tone decreases continuously with increase in jet Mach number. However, for a supersonic jet issued from a bevelled nozzle or a convergent-divergent nozzle with straight side walls, the shock cell structure and the screech frequency pattern are fairly complicated and have not been predicted before. In this paper, it is shown that the shock cell structures of these jets can be decomposed into waveguide modes of the jet flow. The screech frequencies are related to the higher-order waveguide modes following the weakest-link screech tone theory. The measured screech frequencies are found to compare well with the predicted screech frequency curves. Tam, Christopher K. W. and Shen, Hao and Raman, Ganesh Langley Research Center NASA-CR-205131, AIAA Paper 95-0143, NAS 1.26:205131 NAG1-1776...
Author: Hassan M. Nagib
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 82
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Using a flapped NACA 0015 airfoil, measurements of static pressure and lift, with and without oscillatory forcing from the leading edge and flap, demonstrated effective separation control and lift enhancement over the range 0.1
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 492
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Author: F. S. Alvi
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ISBN:
Category :
Languages : en
Pages :
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 920
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