Implicit Finite-Difference Simulations of Three-Dimensional Compressible Flow

Pulliam, Thomas H.; Steger, J. L.

doi:10.2514/3.50745

Cited by 638 publications

(132 citation statements)

References 23 publications

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“…(1), the higher order terms of É and H are neglected. The conventional 3D Navier-Stokes (NS) code can be modified easily by changing the metric terms, 11) such as $ x , $ y , $ z , etc., which transform the 3D NS equations in the xyz coordinate system into the computational space ð$; ; Þ, namely, …”

Section: Methodsmentioning

confidence: 99%

Subsonic and Transonic Flow Simulation for a Wing Oscillating in Yaw and Sideslip

Isogai

2016

Trans. Japan Soc. Aero. S Sci.

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As is well known, the T-tail flutter speed depends strongly on the steady lift or dihedral angle of the horizontal tail plane. The unsteady rolling moment acting on the horizontal tail plane oscillating in yaw and sideslip plays a critical role in this phenomenon. In this paper, a numerical method based on 3D Navier-Stokes equations for computing the subsonic and transonic flow for a wing oscillating in yaw and sideslip is presented. By introducing a new coordinate system oscillating in yaw and sideslip, the existing 3D Navier-Stokes code is easily modified to account for the in-plane motions. The calculated rolling moments show good agreement with the existing experimental data obtained for incompressible flow, and the effect of compressibility, especially the effects of the shock wave in transonic flow, on the rolling moment are clarified.

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Section: Methodsmentioning

confidence: 99%

Subsonic and Transonic Flow Simulation for a Wing Oscillating in Yaw and Sideslip

Isogai

2016

Trans. Japan Soc. Aero. S Sci.

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“…When the flow separation is not significant, or the normal gradient of the stress terms is significantly greater than the stream-wise and circumferential gradients, the thin-layer approximation can be used [22,30,31]. This approach neglects stream-wise (ξ) and circumferential (ζ) viscous terms, and thus only considers normal (η) viscous fluxes.…”

Section: Thin-layer Approximationmentioning

confidence: 99%

Numerical Investigation into Effects of Viscous Flux Vectors on Hydrofoil Cavitation Flow and Its Radiated Flow Noise

2018

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Abstract:In this study, cavitation flow around a hydrofoil and its radiated hydro-acoustic fields were numerically investigated, with an emphasis on the effects of viscous flux vectors. The full three-dimensional unsteady compressible Reynolds-averaged Navier-Stokes equations were numerically solved. The mass transfer model was adopted to model phase changes between liquid water and vapor. To resolve the numerical instability problem arising from the rapid changes in local density and speed of sound of the mixture, the preconditioning and dual-time stepping methods were employed. The filter-based turbulent model was applied to resolve the unstable cavitation flow field more accurately. In splitting the viscous terms, three approaches for dealing with viscous flux vectors were considered: the so-called viscous lagging, full viscous, and thin-layer models. Radiated hydro-acoustic waves were predicted by applying the Ffowcs Williams and Hawkings equations. The effects of the viscous flux vectors on the predicted flow fields and its radiated noise were then examined by comparing the hydro-dynamic forces, velocity distribution, volume fraction, far-field sound directivities, and sound spectrum of the three approaches. The results revealed that the thin-layer model can provide predictions as accurate as the full viscous model, but required less computational time.

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“…Steady and time-accurate solutions can be calculated on structured block or Chimera overset grids. OVERFLOW includes several turbulence models and incorporates various numerical schemes developed from previous research codes such as ARC2D [10] as well as other earlier flow solvers. Various zero-, one-, and two-equation turbulence models are available in OVERFLOW.…”

Section: Flow Solver and Grid Generationmentioning

confidence: 99%

CFD analysis of rotating two-bladed flatback wind turbine rotor.

Dam

Chao²,

Berg

2008

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The effects of modifying the inboard portion of the NREL Phase VI rotor using a thickened, flatback version of the S809 design airfoil are studied using a threedimensional Reynolds-averaged Navier-Stokes method. A motivation for using such a thicker airfoil design coupled with a blunt trailing edge is to alleviate structural constraints while reducing blade weight and maintaining the power performance of the rotor. The calculated results for the baseline Phase VI rotor are benchmarked against wind tunnel results obtained at 10, 7, and 5 meters per second. The calculated results for the modified rotor are compared against those of the baseline rotor. The results of this study demonstrate that a thick, flatback blade profile is viable as a bridge to connect structural requirements with aerodynamic performance in designing future wind turbine rotors.3

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Implicit Finite-Difference Simulations of Three-Dimensional Compressible Flow

Cited by 638 publications

References 23 publications

Subsonic and Transonic Flow Simulation for a Wing Oscillating in Yaw and Sideslip

Subsonic and Transonic Flow Simulation for a Wing Oscillating in Yaw and Sideslip

Numerical Investigation into Effects of Viscous Flux Vectors on Hydrofoil Cavitation Flow and Its Radiated Flow Noise

CFD analysis of rotating two-bladed flatback wind turbine rotor.

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