Computational/experimental investigation of staged injection into a Mach 2 flow

The stage normal injection of two jets of air into a Mach 2 freestream behind a rearward-facing step has been investigated using laser-induced iodine fluorescence and laser doppler anemometry techniques. A detailed data set has been compiled that includes profiles of pressure, temperature, two compo...

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Bibliographic Details
Published in:AIAA journal 1994-05, Vol.32 (5), p.907-916
Main Authors: Eklund, D. R, Fletcher, D. G, Hartfield, R. J, McDaniel, J. C, Northam, G. B, Dancey, C. L, Wang, J. A
Format: Article
Language:English
Subjects:
420400 - Engineering- Heat Transfer & Fluid Flow
990200 - Mathematics & Computers
Aerodynamics
Compressible flows
shock and detonation phenomena
COMPUTERIZED SIMULATION
DIFFERENTIAL EQUATIONS
ENGINEERING
EQUATIONS
Exact sciences and technology
Fluid dynamics
FLUID FLOW
Fluid Mechanics And Heat Transfer
Fundamental areas of phenomenology (including applications)
GENERAL AND MISCELLANEOUS//MATHEMATICS, COMPUTING, AND INFORMATION SCIENCE
Jets
MESH GENERATION
NAVIER-STOKES EQUATIONS
NUMERICAL SOLUTION
PARTIAL DIFFERENTIAL EQUATIONS
Physics
SIMULATION
Supersonic and hypersonic flows
SUPERSONIC FLOW
TURBULENT FLOW
Turbulent flows, convection, and heat transfer
Wind
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Summary:The stage normal injection of two jets of air into a Mach 2 freestream behind a rearward-facing step has been investigated using laser-induced iodine fluorescence and laser doppler anemometry techniques. A detailed data set has been compiled that includes profiles of pressure, temperature, two components of velocity, and mole fraction of the injectant at 44 locations, plus planar surveys of pressure, temperature, velocity, and mole fraction. A companion numerical study was performed using the SPARK Navier-Stokes code. Good overall agreement was observed for this complex, highly three-dimensional flowfield. Discrepancies were observed in the computed and measured total temperatures, turbulent mixing, and shock strengths. The effect of grid resolution was investigated by calculating solutions on grids of 60,000 points, 200,000 points, and 450,000 points. Differences in the solutions on the two finer grids were small. The effect of turbulence modeling was investigated by calculating solutions with three different algebraic models for the jet turbulence. Overall, the turbulence models were found to have the greatest effect on the numerical solutions, followed by the grid resolution and the injectant Mach number.
ISSN:0001-1452
1533-385X
DOI:10.2514/3.12073