Direct Numerical Simulation of Nozzle-Wall Pressure Fluctuations in a Mach 8 Wind Tunnel

Duan, Lian; Nicholson, Gary L.; Huang, Juan; Casper, Katya M.; Wagnild, Ross; Bitter, Neal

doi:10.2514/6.2019-0874

Cited by 7 publications

(1 citation statement)

References 20 publications

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“…The simulation involves a single domain with a long streamwise box, as illustrated in Figure 1. A detailed description of the problem formulation, the numerical scheme, and the initial and boundary conditions can be found in References [13,[18][19][20][21][22]. The validity of the numerical methods and procedures have been established in multiple previous publications [10,18,21,22].…”

Section: Dns Simulation Of Hypersonic Turbulent Boundary Layersmentioning

confidence: 99%

Assessment of Turbulence Models in a Hypersonic Cold-Wall Turbulent Boundary Layer

Huang

Bretzke

Duan

2019

Fluids

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In this study, the ability of standard one- or two-equation turbulence models to predict mean and turbulence profiles, the Reynolds stress, and the turbulent heat flux in hypersonic cold-wall boundary-layer applications is investigated. The turbulence models under investigation include the one-equation model of Spalart–Allmaras, the baseline k - ω model by Menter, as well as the shear-stress transport k - ω model by Menter. Reynolds-Averaged Navier-Stokes (RANS) simulations with the different turbulence models are conducted for a flat-plate, zero-pressure-gradient turbulent boundary layer with a nominal free-stream Mach number of 8 and wall-to-recovery temperature ratio of 0.48 , and the RANS results are compared with those of direct numerical simulations (DNS) under similar conditions. The study shows that the selected eddy-viscosity turbulence models, in combination with a constant Prandtl number model for turbulent heat flux, give good predictions of the skin friction, wall heat flux, and boundary-layer mean profiles. The Boussinesq assumption leads to essentially correct predictions of the Reynolds shear stress, but gives wrong predictions of the Reynolds normal stresses. The constant Prandtl number model gives an adequate prediction of the normal turbulent heat flux, while it fails to predict transverse turbulent heat fluxes. The discrepancy in model predictions among the three eddy-viscosity models under investigation is small.

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Section: Dns Simulation Of Hypersonic Turbulent Boundary Layersmentioning

confidence: 99%

Assessment of Turbulence Models in a Hypersonic Cold-Wall Turbulent Boundary Layer

Huang

Bretzke

Duan

2019

Fluids

Self Cite

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Direct Numerical Simulation of Acoustic Disturbances in a Hypersonic Two-Dimensional Nozzle Configuration

Hildebrand¹,

Choudhari²,

Deegan

et al. 2022

AIAA Journal

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Reynolds-Number Effects on the Acoustic Disturbance Environment in a Mach 6 Nozzle

Hildebrand,

Choudhari,

Duan

2023

AIAA Journal

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To understand the impact of the Reynolds number on the disturbance field inside a high-speed wind tunnel, we use direct numerical simulations to model turbulent boundary layers along the walls of a quasi-two-dimensional nozzle configuration. These simulations are performed at four different unit Reynolds numbers, ranging from [Formula: see text] to [Formula: see text]. The predominantly hydrodynamic fluctuations inside the boundary layer are nearly unaffected by the freestream forcing of the impinging acoustic radiation from the opposite wall. Within the nozzle-core region, the disturbance environment is found to be spatially uniform and solely acoustic in character. Comparisons with tunnel noise measurements are made using the numerical data. For the first time, comparisons of fluctuations in the same physical quantity (the streamwise mass flux) have been published, as opposed to earlier comparisons involving static-pressure fluctuations based on the simulations and pitot-pressure fluctuations recorded in the wind tunnel. The NASA 20 in. Mach 6 wind tunnel observations corroborate the predicted trend of decreased root-mean-square variations in pressure and mass flux as the Reynolds number rises. Additional details of the acoustic radiation field are quantified and should be useful toward a digital synthesis of the tunnel disturbance environment that would enable realistic simulations of the natural transition process.

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Direct Numerical Simulation of Nozzle-Wall Pressure Fluctuations in a Mach 8 Wind Tunnel

Cited by 7 publications

References 20 publications

Assessment of Turbulence Models in a Hypersonic Cold-Wall Turbulent Boundary Layer

Assessment of Turbulence Models in a Hypersonic Cold-Wall Turbulent Boundary Layer

Direct Numerical Simulation of Acoustic Disturbances in a Hypersonic Two-Dimensional Nozzle Configuration

Reynolds-Number Effects on the Acoustic Disturbance Environment in a Mach 6 Nozzle

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