Computing axisymmetric jet screech tones using unstructured grids
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Computing axisymmetric jet screech tones using unstructured grids

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Published by National Aeronautics and Space Administration, Glenn Research Center, Available from the NASA Center for Aerospace Information, National Technical Information Service [distributor in [Cleveland, Ohio], Hanover, MD, Springfield, VA .
Written in English

Subjects:

  • Unstructured grids.,
  • Screech tones.,
  • Aeroacoustics.,
  • Axisymmetric flow.,
  • Nozzle geometry.

Book details:

Edition Notes

StatementPhilip C.E. Jorgenson, Ching Y. Loh ; prepared for the 38th Joint Propulsion Conference and Exhibit sponsored by the AIAA, ASME, SAE, and ASEE, Indianapolis, Indiana, July 7-10, 2002.
SeriesNASA/TM -- 2002-211799., NASA technical memorandum -- 211799.
ContributionsLoh, Ching Y. 1944-, NASA Glenn Research Center.
The Physical Object
FormatMicroform
Pagination1 v.
ID Numbers
Open LibraryOL16098758M

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Download Citation | Computing Axisymmetric Jet Screech Tones Using Unstructured Grids | The space-time conservation element and solution element (CE/SE) method is . The equations are time marched to predict the unsteady flow and the near-field screech tone noise issuing from an underexpanded circular jet. The CE/SE method uses an unstructured grid based data structure. The unstructured grids for these calculations are generated based on the method of Delaunay triangulation. The purpose of this paper is to. Computing Axisymmetric Jet Screech Tones using Unstructured Grids The purpose of this paper is to show that computations with an aeroacoustic feedback loop, the jet screech noise, can be obtained using truly unstructured grid technology. Numerical results are presented for a nozzle with two different lip thicknesses which will be referred to in this paper as a thin and a thick lip nozzle. AIAA COMPUTING AXISYMMETRIC JET SCREECH TONES USING UNSTRUCTURED GRIDS. The CE/SE method uses an unstructured grid based data structure. The unstructured grids for these calculations are generated based on the method of Delaunay triangulation. The purpose of this paper is to show that an acoustics solution with a feedback loop.

Computing Axisymmetric Jet Screech Tones Using Unstructured Grids. The purpose of this paper is to show that an acoustics solution with a feedback loop can be obtained using truly unstructured grid technology. Numerical results are presented for two different nozzle geometries. The first is considered to have a thin nozzle lip and the.   1. A. Powell, “ On the noise emanating from a two-dimensional jet above the critical pressure,” Aeronaut.Q. 4, ().Google Scholar Crossref; 2. H. Shen and C. K. W. Tam, “ Numerical simulation of the generation of axisymmetric mode jet screech tones,” AIAA J. 36, (). Google Scholar Crossref; 3. A. T. Thies and C. K. W. Tam, “ Computational of turbulent axisymmetric . Computing Axisymmetric Jet Screech Tones using Unstructured Grids. By Ching Y. Loh and Philip C. E. Jorgenson. Abstract. The purpose of this paper is to show that computations with an aeroacoustic feedback loop, the jet screech noise, can be obtained using truly unstructured grid technology. Numerical results are presented for a nozzle with. The source locations of axisymmetric modes of screech tones are numerically investigated. Fourth-order optimized compact scheme and fourth-order Runge–Kutta method are .

The periodic oscillation of the shock waves in screeching, underexpanded, supersonic jets, issuing from a choked, axisymmetric, nozzle at fully expanded Mach numbers (M j) of and , is studied experimentally and experimental part uses schlieren photography and a new shock detection technique which depends on a recently observed phenomenon of laser light scattering by. Computing Axisymmetric Jet Screech Tones Using Unstructured Grids. block communication becomes dicult for parallel computing and solving real engineering problems. The underexpanded. A new passive control technique of cavity-induced pressure oscillations has been investigated numerically for a supersonic two-dimensional flow over open rectangular cavities at Mac h number at the cavity entrance. A subcavity on the front wall of the cavity covered by a flat plate was evaluated for the effectiveness of controlling cavity-induced acoustic oscillations. Computing Axisymmetric Jet Screech Tones Using Unstructured Grids many researchers carried out numerical simulations of screech tones by virtue of advanced computing powers. Jet Screech.