Modeling scramjet combustor flowfields with a grid adaptation scheme

Journal Article · Sun May 01 00:00:00 EDT 1994 · AIAA Journal (American Institute of Aeronautics and Astronautics); (United States)

DOI:https://doi.org/10.2514/3.12076· OSTI ID:6979681

Ramakrishnan, R; Singh, D J ^[1]

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1. Analytical Services and Materials, Inc., Hampton, VA (United States)

The accurate description of flow features associated with the normal injection of fuel into supersonic primary flows is essential in the design of efficient engines for hypervelocity aerospace vehicles. The flow features in such injections are complex with multiple interactions between shocks and between shocks and boundary layers. Numerical studies of perpendicular sonic N2 injection and mixing in a Mach 3.8 scramjet combustor environment are discussed. A dynamic grid adaptation procedure based on the equilibration of spring-mass systems is employed to enhance the description of the complicated flow features. Numerical results are compared with experimental measurements and indicate that the adaptation procedure enhances the capability of the modeling procedure to describe the flow features associated with scramjet combustor components. 14 refs.

• OSTI ID: 6979681
• Journal Information: AIAA Journal (American Institute of Aeronautics and Astronautics); (United States), Vol. 32:5; ISSN 0001-1452
• Country of Publication: United States
• Language: English

Related Subjects

42 ENGINEERING
99 GENERAL AND MISCELLANEOUS//MATHEMATICS, COMPUTING, AND INFORMATION SCIENCE
NAVIER-STOKES EQUATIONS
NUMERICAL SOLUTION
SUPERSONIC FLOW
BOUNDARY LAYERS
COMPUTERIZED SIMULATION
COMBUSTION CHAMBERS
MESH GENERATION
NITROGEN
DIFFERENTIAL EQUATIONS
ELEMENTS
EQUATIONS
FLUID FLOW
LAYERS
NONMETALS
PARTIAL DIFFERENTIAL EQUATIONS
SIMULATION
420400* - Engineering- Heat Transfer & Fluid Flow
990200 - Mathematics & Computers