Analysis tool for application to ground testing of highly underexpanded nozzles

Cooper, G. K.; Jordan, Jeffrey M.; Phares, W. J.

doi:10.2514/6.1987-2015

Cited by 12 publications

(3 citation statements)

References 4 publications

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“…Pulliam [7] later added the artificial dissipation of Jameson et al [8] and called the code ARC3D. Cooper et al [9] adapted the code for internal flows of propulsion application and named the code PARC3D which was subsequently renamed NPARC when an alliance was formed between NASA LeRC and AEDC to jointly develop and support the code. NPARC solves the full three-dimensional Reynoldsaveraged Navier-Stokes equations in strong conservation form using Beam and Warming [10] approximate factorization.…”

Section: Methodsmentioning

confidence: 99%

Computational study of flow in a rocket-based combined cycle (RBCC) engine inlet

Reddy

Sree

2006

Computers & Fluids

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Section: Methodsmentioning

confidence: 99%

Computational study of flow in a rocket-based combined cycle (RBCC) engine inlet

Reddy

Sree

2006

Computers & Fluids

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“…The code was originally developed as AIR3D by Pulliam and Steger (1980), and Pulliam (1984) later added the artificial dissipation of Jameson (Jameson et al, 1981) and called the code ARC3D. Cooper et al (1987) adapted the code for internal flows of propulsion application and named the code PARC3D which was subsequently renamed NPARC when an alliance was formed between NASA LeRC and AEDC to jointly develop and support the code.…”

Section: Methodsmentioning

confidence: 99%

Computation of 3-D Compressible Flow From a Rectangular Nozzle With Delta Tabs

Reddy

Steffen

Zaman

1997

Volume 1: Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery

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A three-dimensional viscous flow analysis is performed using a time-marching Reynolds-averaged Navier-Stokes code for a 3:1 rectangular nozzle with two delta tabs located at the nozzle exit plane to enhance mixing. Two flow configurations, a subsonic jet case and a supersonic jet case using the same tab configuration which were previously studied experimentally, are computed and compared with the experimental data. The experimental data include streamwise velocity and vorticity distributions for the subsonic case, and Mach number distributions for the supersonic case, at various axial locations downstream of the nozzle exit. The computational results show very good agreement with the experimental data. In addition, the effect of compressibility on vorticity dynamics are examined by comparing the vorticity contours of the subsonic jet case with those of the supersonic jet case which were not measured in the experiment.

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“…The supersonic flow inside a nozzle is adjusted by interacting with ambient condition through the subsonic boundary layer in a nozzle [1]. It is very essential in designing small thrusters used for the attitude control of satellites to look into the physical phenomenon of a plume minutely.…”

Section: Introductionmentioning

confidence: 99%

Numerically analyzed supersonic flow structure behind the exit of a two-dimensional micro nozzle

Kim

Choi

et al. 2008

J Mech Sci Technol

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The compressible flow field is numerically analyzed in a two-dimensional converging-diverging nozzle of which the area ratio, exit to throat, is 1.8. The solver is FLUENT and the embedded RNG k ε − model is adopted to simulate turbulent flow. The plume characteristics such as shock-cell structure are discussed when nozzle pressure ratio and stagnation temperature at the nozzle entrance are varied. The downstream flow field can be classified into two types based on the shock shapes generated near the nozzle exit. First, a reiterative pattern in the plume is not formed between the slip streams in case that a strong lambda-type shock wave exists. Second, when oblique shock waves are crossing each other on the nozzle centerline, a shock cell structure appears in the plume field. Even when the flow field is changed due to stagnation temperature, the upstream of the shock wave is little affected. Especially, the pressure distributions on the nozzle centerline behind the shock wave are rarely influenced by the stagnation temperature, that is, the product of density and temperature is nearly constant provided that the working fluid is a perfect gas. Therefore, the pressure field shows quasi-isobaric behavior far downstream.

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Analysis tool for application to ground testing of highly underexpanded nozzles

Cited by 12 publications

References 4 publications

Computational study of flow in a rocket-based combined cycle (RBCC) engine inlet

Computational study of flow in a rocket-based combined cycle (RBCC) engine inlet

Computation of 3-D Compressible Flow From a Rectangular Nozzle With Delta Tabs

Numerically analyzed supersonic flow structure behind the exit of a two-dimensional micro nozzle

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