Measurements of interactions between acoustic fields and nonuniform mean flow
Abstract
Two problems crucial to the stability of longitudinal acoustic waves in solid rocket motors are examined experimentally. The first is the dissipation of energy associated with an average flow inward at the lateral boundary. Measurements reported here, though subject to considerable experimental error, show that the actual losses are much larger than predicted by the approximate one dimensional analysis. The second problem is the attenuation of waves accompanying reflection by the nonuniform flow in a choked exhaust nozzle. Empahsis in this work has been on technique, to provide data relatively easily and inexpensively. It appears that good results can be obtained in a routine manner using small supersonic wind tunnel operated as an open cycle. At least for Mach numbers up to 0.04 at the nozzle entrance, difficulties with signal/noise are satisfactorily overcome with a tracking filter.
Additional Information
Unclassified; No Copyright; Unlimited; Publicly available. NASA Center: NASA (non Center Specific). Publication Year: 1980. Added to NTRS: 2005-10-10. Work supported by the Air Force Rocket Propulsion Laboratory. In NASA. Langley Research Center The 17th JANNAF Combust. Meeting, Vol. 1 p 321-336 (SEE N81-16253 07-28). No digital version available. Reference in Nasa Technical Reports Server (NTRS)Attached Files
Accepted Version - 266_Magiawala_K_1981.pdf
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Additional details
- Eprint ID
- 21243
- Resolver ID
- CaltechAUTHORS:20101208-114247352
- Air Force Rocket Propulsion Laboratory
- Created
-
2010-12-14Created from EPrint's datestamp field
- Updated
-
2019-10-03Created from EPrint's last_modified field
- Caltech groups
- Guggenheim Jet Propulsion Center, GALCIT
- Series Name
- NASA Reports
- Series Volume or Issue Number
- NTRS: 2005-10-10
- Other Numbering System Name
- Document ID
- Other Numbering System Identifier
- 19810007754