Numerical study of supersonic combustors by multi-block grids with mismatched interfaces
- Moon, Young J.
- Oct 1, 1990.
- Physical Description:
- 1 electronic document
- Restrictions on Access:
- Unclassified, Unlimited, Publicly available.
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- A three dimensional, finite rate chemistry, Navier-Stokes code was extended to a multi-block code with mismatched interface for practical calculations of supersonic combustors. To ensure global conservation, a conservative algorithm was used for the treatment of mismatched interfaces. The extended code was checked against one test case, i.e., a generic supersonic combustor with transverse fuel injection, examining solution accuracy, convergence, and local mass flux error. After testing, the code was used to simulate the chemically reacting flow fields in a scramjet combustor with parallel fuel injectors (unswept and swept ramps). Computational results were compared with experimental shadowgraph and pressure measurements. Fuel-air mixing characteristics of the unswept and swept ramps were compared and investigated.
- Other Subject(s):
- NASA Technical Reports Server (NTRS) Collection.
- Document ID: 19910002440.
Accession ID: 91N11753.
AIAA PAPER 90-5204.
National Aerospace Planes Conference; 29-31 Oct. 1990; Orlando, FL; United States.
- No Copyright.
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