Numerical Benchmark for High-Reynolds-Number Supercritical Flows with Large Density Gradients

Because of the extreme complexity of physical phenomena at high pressure, only limited data are available for solver validation at device-relevant conditions such as liquid rocket engines, gas turbines, or diesel engines. In the present study, a two-dimensional direct numerical simulation is used to...

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Bibliographic Details
Published in:AIAA journal 2016-05, Vol.54 (5), p.1445-1460
Main Authors: Ruiz, A. M, Lacaze, G, Oefelein, J. C, Mari, R, Cuenot, B, Selle, L, Poinsot, T
Format: Article
Language:English
Subjects:
Benchmarking
Benchmarks
Boundary conditions
Computational fluid dynamics
Density gradients
Density ratio
Diesel engines
Direct numerical simulation
Engineering
Engineering Sciences
Engines
Flow characteristics
Fluid flow
Fluids mechanics
Gas turbine engines
Gas turbines
High Reynolds number
Liquids
Mathematical models
Mechanics
Numerical prediction
Reynolds number
Rocket engines
Rockets
Solvers
Supercritical flow
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Summary:Because of the extreme complexity of physical phenomena at high pressure, only limited data are available for solver validation at device-relevant conditions such as liquid rocket engines, gas turbines, or diesel engines. In the present study, a two-dimensional direct numerical simulation is used to establish a benchmark for supercritical flow at a high Reynolds number and high-density ratio at conditions typically encountered in liquid rocket engines. Emphasis has been placed on maintaining the flow characteristics of actual systems with simple boundary conditions, grid spacing, and geometry. Results from two different state-of-the-art codes, with markedly different numerical formalisms, are compared using this benchmark. The strong similarity between the two numerical predictions lends confidence to the physical accuracy of the results. The established database can be used for solver benchmarking and model development at conditions relevant to many propulsion and power systems.
ISSN:0001-1452
1533-385X
DOI:10.2514/1.J053931