Flow-Turning Losses in Solid Rocket Motors.
Abstract
Results are presented of an experimental and analytical investigation of the flow-turning losses resulting from the injection of ambient air into an acoustically energized duct. Measurements show that acoustic energy is absorbed. In all test cases, however, the sound energies absorbed by the finite admittance duct side walls were significantly larger than that absorbed by the injected flows. One dimensional steady state and transient flow-turning solutions were derived. For the special case of rigid walls and low injection rates, the steady-state solutions showed that the flow-turning losses were approximately equal to 10 Log (1-Mav) where Mav is the average Mach number across the duct cross-section. The one-dimensional solutions inadequately predicted the measured acoustic energy losses. The transient solutions compared very favorably with Culick's model. Both estimated almost the same decay constants. Sound absorption, Sound attenuation, Sound flow acoustic losses, Combustion instability. (mjm)
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1988
- Accession Number
- ADA206099
Entities
People
- Alan S. Hersh
- Jin Tso