Accession Number:

ADA172868

Title:

Numerical Study of Flow Turning Phenomenon.

Descriptive Note:

Memorandum rept.,

Corporate Author:

NAVAL RESEARCH LAB WASHINGTON DC

Personal Author(s):

• Baum,Joseph D.

Report Date:

1986-10-10

Pagination or Media Count:

45.0

Abstract:

The objective of the present research work is an understanding of the physical mechanisms by which energy is exchanged between the mean and acoustic flow fields in resonant combustion chambers in particular, solid rocket motors. These processes may alter the balance between sources and sinks of oscillatory energy in the combustor significantly and thus are critical to our ability to predict the stability characteristics of proposed motor designs. The present report concentrates on the description and analysis of the computational results obtained to date in the study of acoustic refraction and flow turning phenomena. Three studies were conducted. The time-dependent compressible Navier Stokes equations were solved utilizing an implicit, non-iterative Linearized Block Implicit scheme. In the first study acoustic wave propagation in a tube with a coexisting sheared mean flow was investigated. The results demonstrate that acoustic refraction effects, i.e., the growth of acoustic pressure near the wall for downstream propagation, are significant., In addition, the results demonstrate acoustic energy transfer to the mean flow as well as Richardsons annular effect. To the best of the authors knowledge these are the first solutions demonstrating either Richardsons annular effect or refraction effects that are obtained through solution of the complete Navier-Stokes equations.

Descriptors:

• *ENERGY TRANSFER
• *COMBUSTION CHAMBERS
• *ROCKET ENGINE NOISE
• GRAPHS
• MASS FLOW
• DATA REDUCTION
• MACH NUMBER
• NAVIER STOKES EQUATIONS
• REYNOLDS NUMBER
• ACOUSTIC FIELDS
• ACOUSTIC REFRACTION

Subject Categories:

• Combustion and Ignition

Distribution Statement:

APPROVED FOR PUBLIC RELEASE