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Computing Axisymmetric Jet Screech Tones Using Unstructured GridsThe space-time conservation element and solution element (CE/SE) method is used to solve the conservation law form of the compressible axisymmetric Navier-Stokes equations. 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 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 second has a thick nozzle lip. Comparisons with available experimental data are shown for flows corresponding to several different jet Mach numbers. Generally good agreement is obtained in terms of flow physics, screech tone frequency, and sound pressure level.
Document ID
20030003705
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Jorgenson, Philip C. E. (NASA Glenn Research Center Cleveland, OH United States)
Loh, Ching Y. (Taitech, Inc. Brook Park, OH United States)
Date Acquired
September 7, 2013
Publication Date
August 1, 2002
Subject Category
Aerodynamics
Report/Patent Number
NASA/TM-2002-211799
Meeting Information
Meeting: 38th Joint Propulsion Conference and Exhibit
Location: Indianapolis, IN
Country: United States
Start Date: July 7, 2002
End Date: July 10, 2002
Sponsors: American Society for Electrical Engineers, American Inst. of Aeronautics and Astronautics, Society of Automotive Engineers, Inc., American Society of Mechanical Engineers
Funding Number(s)
PROJECT: RTOP 708-90-43
Distribution Limits
Public
Copyright
Public Use Permitted.

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