NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Analysis of Inlet-Compressor Acoustic Interactions Using Coupled CFD CodesA problem that arises in the numerical simulation of supersonic inlets is the lack of a suitable boundary condition at the engine face. In this paper, a coupled approach, in which the inlet computation is coupled dynamically to a turbomachinery computation, is proposed as a means to overcome this problem. The specific application chosen for validation of this approach is the collapsing bump experiment performed at the University of Cincinnati. The computed results are found to be in reasonable agreement with experimental results. The coupled simulation results could also be used to aid development of a simplified boundary condition.
Document ID
19990019479
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Suresh, A. (DYNACS Engineering Co., Inc. Brook Park, OH United States)
Townsend, S. E. (DYNACS Engineering Co., Inc. Brook Park, OH United States)
Cole, G. L. (NASA Lewis Research Center Cleveland, OH United States)
Slater, J. W. (NASA Lewis Research Center Cleveland, OH United States)
Chima, R. (NASA Lewis Research Center Cleveland, OH United States)
Date Acquired
September 6, 2013
Publication Date
December 1, 1998
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA Paper 98-0749
NASA/TM-1998-208839
E-11451
NAS 1.15:208839
Meeting Information
Meeting: Aerospace Sciences
Location: Reno, NV
Country: United States
Start Date: January 11, 1999
End Date: January 14, 1999
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
PROJECT: RTOP 509-10-11
CONTRACT_GRANT: NAS3-98008
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

There are no records associated with this record.
No Preview Available