CFD validation for base flows with and without plume interaction

Bakker, P.G.; Bannink, W.J.; Servel, Patrick; Reijasse, Philippe

doi:10.2514/6.2002-438

Cited by 13 publications

(11 citation statements)

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“…An original version of the model without adjustable nozzle length was used within the framework of the Future European Space Transportation Investigation Program (known as FESTIP) [31] and has been tested extensively in a series of experimental and numerical assessments (e.g., Refs. [12,[32][33][34]). The jet conditions are selected based on the exhaust conditions of the Ariane 5 Vulcain 2 engine, and they are shown in Table 2.…”

Section: A Flow Configuration and Modelmentioning

confidence: 99%

Effects of Exhaust Plume and Nozzle Length on Compressible Base Flows

et al. 2019

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The effects of an exhaust plume and nozzle length on the flow organization of axisymmetric base flows have been studied experimentally at Mach numbers of 0.76 and 2.2 using particle image velocimetry. From the measured velocity data, the mean pressure field was computed. The application of different nozzle lengths resulted in flow cases in which the shear layer impinges on the model, on the flow downstream of the model, or intermittently on the model and on the flow. The results showed that, for intermediate nozzle lengths, the overall pressure level downstream of the base decreased in the transonic flow cases and increased in the supersonic flow cases, indicating an entrainment effect in transonic flow and a displacement effect in supersonic flow. An increase in nozzle length was found to lead to a higher local pressure at the nozzle exit, which seemed to result in more overexpanded plumes in the transonic flow cases and less underexpanded plumes in the supersonic flow cases.

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Section: A Flow Configuration and Modelmentioning

confidence: 99%

Effects of Exhaust Plume and Nozzle Length on Compressible Base Flows

et al. 2019

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“…Research on 3D simulation of base flow in the presence of a propulsive jet and a support sting is very limited in the open literature. Bakker et al [22] simulated the experimental condition of Bannink et al [8]. Two sets of numerical simulations, namely:…”

Section: Introductionmentioning

confidence: 99%

Simulation of supersonic base flow: Effect of computational grid and turbulence model

Dharavath

Sinha

Chakraborty

2009

Proceedings of the Institution of Mechanical Engineers, Part G:

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The supersonic base flow of a blunted cone-cylinder rocket model in the presence of a central propulsive jet is investigated numerically by solving three-dimensional Reynolds averaged Navier-Stokes equations in an unstructured mesh using a commercial computational fluid dynamics software. The effect of the computational grid and the turbulence model in predicting the radial variation of base pressure has been brought out. Very fine grid ( y + ∼ 2) is required to correctly predict the base pressure. The renormalized group k−ε turbulence model performs better compared to the k-ω turbulence model in predicting the base pressure. It was observed that the base flow characteristics in the lower and upper portions of the base are significantly different due to the influence of model support.

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“…There have been various CFD studies for the prediction of base flows and most of them used Reynolds-averaged Navier-Stokes (RANS) simulations with RANS turbulence models to handle high Reynolds number flows. Many investigations with various RANS turbulence models have tried to predict the supersonic cylindrical base flow [13][14][15][16], an axisymmetric truncated plug nozzle [17,18], and blunted cone cylinder [19]. Some improvements of the predictability have been made, but unfortunately the RANS simulations have failed to produce quantitative prediction of the base flow.…”

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confidence: 98%

Time-Series and Time-Averaged Characteristics of Subsonic to Supersonic Base Flows

Kawai

Fujii

2007

AIAA Journal

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Physics of cylindrical base flows ranging from subsonic to supersonic speeds at zero angle of attack are computationally investigated. Time-series and time-averaged investigations of base flows show distinctive characteristics at subsonic, transonic, and supersonic regimes. Normalized time-averaged base pressure decreases proportionally with respect to increasing freestream dynamic pressure in the subsonic regime of M 1 < 0:8. The base pressure begins to fall rapidly in the transonic regime and then settles down and decreases gradually toward an asymptotic value at M 1 > 1:5. Normalized base pressure fluctuations sharply increase at transonic speeds, whereas they decrease with increasing freestream Mach number at subsonic and supersonic speeds. Appearance of unsteady local shock waves change the characteristics of base pressure distinctively at the transonic speeds. Spectra of the base pressure show one clear peak at subsonic speeds (related to the shear layer dynamics), two clear peaks at transonic speeds (related to the shear layer dynamics and its subharmonic), and three major peaks at supersonic speeds (related to the shear layer dynamics, its subharmonic, and an additional mechanism). Instability of the free shear layers has dominant influence on the overall base flowfield over a wide range of Mach numbers ranging from subsonic to supersonic speeds. However, at supersonic speeds, an additional mechanism of instability within the recirculating region is possibly at work and has dominant influence on the flowfield. The dominant mechanisms significantly cause the strong Mach number dependence of the high-pressure region which is strongly related to the base pressure. The spectrum analysis suggests that the substantial base pressure fluctuations are caused by the pulsing of the flow inside the recirculating region. Nomenclature a = sonic speed C K = Yoshizawa model coefficientfrom closest wall to blending position d wall = distance from closest wall M = local Mach number Pr t = turbulent Prandtl number p = local static pressure q = local dynamic pressure q j = heat flux vector R = cylinder base radius Re = Reynolds number S ij = strain rate tensor Sr = Strouhal number T = temperature u = axial velocityx, y, z = Cartesian coordinates x j = coordinate vector = ratio of specific heats filter = filter length scale t = integration time x, y, z = step size of the grid in x, y, z directions ij = Kronecker delta t = turbulent eddy viscosity = kinematic eddy viscosity = density = blending function Superscripts LES = quantity in large-eddy simulation formulation RANS = quantity in Reynolds-averaged Navier-Stokes formulation = dimensional quantity = spatial-filtered or ensemble-averaged quantitỹ = Favre-filtered or Favre-averaged quantity = wall unit quantity Subscripts 1 = freestream quantity

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CFD validation for base flows with and without plume interaction

Cited by 13 publications

References 1 publication

Effects of Exhaust Plume and Nozzle Length on Compressible Base Flows

Effects of Exhaust Plume and Nozzle Length on Compressible Base Flows

Simulation of supersonic base flow: Effect of computational grid and turbulence model

Time-Series and Time-Averaged Characteristics of Subsonic to Supersonic Base Flows

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