Investigation of Structured and Unstructured Grid Topology and Resolution Dependence for Scale-Resolving Simulations of Axisymmetric Detaching-Reattaching Shear Layers

Schumann, Jan-Erik; Hannemann, Volker; Hannemann, Klaus

doi:10.1007/978-3-030-27607-2_13

Cited by 6 publications

(7 citation statements)

References 10 publications

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“…In former investigations (e.g. [14]) the IDDES approach showed results of higher fidelity that agree well with experimental reference data regarding overall flow field, reattachment length and pressure distributions and thus are considered more accurate with respect to these quantities. This is also supported by the above argument of IDDES being less affected by turbulence modelling parameters than RANS.…”

Section: Investigation Of Aft-body Flow Fieldssupporting

confidence: 64%

“…To ensure a sufficient grid resolution for the scale resolving simulations a grid sensor is used. This sensor computes the ratio between resolved and modelled turbulent kinetic energy and was shown to accurately display regions of underresolution in previous investigations of similar flows and grid topologies [14]. A sensor value of 0.8 is considered to be sufficient to capture important flow phenomena and, as shown on the right of Fig.…”

Section: Investigation Of Aft-body Flow Fieldsmentioning

confidence: 94%

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Numerical Investigation of Space Launch Vehicle Base Flows with Hot Plumes

Schumann

Fertig

Hannemann

et al. 2020

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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The flow field around generic space launch vehicles with hot exhaust plumes is investigated numerically. Reynolds-Averaged Navier-Stokes (RANS) simulations are thermally coupled to a structure solver to allow determination of heat fluxes into and temperatures in the model structure. The obtained wall temperatures are used to accurately investigate the mechanical and thermal loads using Improved Delayed Detached Eddy Simulations (IDDES) as well as RANS. The investigated configurations feature cases both with cold air and hot hydrogen/ water vapour plumes as well as cold and hot wall temperatures. It is found that the presence of a hot plume increases the size of the recirculation region and changes the pressure distribution on the nozzle structure and thus the loads experienced by the vehicle. The same effect is observed when increasing the wall temperatures. Both RANS and IDDES approaches predict the qualitative changes between the configurations, but the reattachment location predicted by IDDES is up to 7% further upstream than that predicted by RANS. Additionally, the heat flux distribution along the nozzle and base surface is analysed and shows significant discrepancies between RANS and IDDES, especially on the nozzle surface and in the base corner.

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Section: Investigation Of Aft-body Flow Fieldssupporting

confidence: 64%

Section: Investigation Of Aft-body Flow Fieldsmentioning

confidence: 94%

Numerical Investigation of Space Launch Vehicle Base Flows with Hot Plumes

Schumann

Fertig

Hannemann

et al. 2020

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

Self Cite

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show abstract

“…To ensure sufficient resolution, a grid sensor [16] is employed. A detailed discussion of the overall grid design as well as an intensive analysis of the grid parameters and validation of the used grid sensors can be found in Schumann et al [18].…”

Section: Test Case Description and Setupmentioning

confidence: 99%

“…The sensitivity of the solution to in-plane and circumferential resolution changes for a configuration without plume was previously investigated [18]. The investigation showed that the circumferential resolution drastically changed the flow field, but it was hypothesized that this behaviour might change when a configuration with an active plume is investigated.…”

Section: Sensitivity To Circumferential Resolutionmentioning

confidence: 99%

Sensitivity of scale resolving aft-body flow simulations to numerical model parameter variations

Schumann

Hannemann

2021

CEAS Space J

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The sensitivity of hybrid RANS-LES methods like Improved Delayed Detached Eddy Simulation (IDDES) to numerical model parameter variations related to generic space launch vehicle aft-body flows is investigated. In particular, the changes resulting from the choice of the time-step size, the turbulence model, the fluid modelling, the circumferential grid resolution, the filter length definition, and the data collection period is considered. The results are also compared to experimental and numerical data taken from the available literature. The sensitivity to the time-step size and the turbulence model is minuscule with respect to the obtained mean flow field, wall pressure distributions, azimuthal modes, and wall pressure frequency spectra. However, circumferential resolution, fluid model, and filter length definition affect the solution to a higher extent. Buffeting spectra are very sensitive to the data collection period.

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“…Figure 9 displays the simulation concept, where RANS equations are solved for the boundary layers attached to the rocket forebody, while aft-body wake flows are represented by LES. The team of project B5 focused on the flow physics of hot plumes and hot walls using numerical simulation [26,27]. For this purpose, the flow solver was coupled to a thermal structure solver to obtain realistic wall temperature distributions.…”

Section: Modeling Of Buffetingmentioning

confidence: 99%

Collaborative Research for Future Space Transportation Systems

Haidn

Adams

Radespiel

et al. 2020

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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This chapter book summarizes the major achievements of the five topical focus areas, Structural Cooling, Aft-Body Flows, Combustion Chamber, Thrust Nozzle, and Thrust-Chamber Assembly of the Collaborative Research Center (Sonderforschungsbereich) Transregio 40. Obviously, only sample highlights of each of the more than twenty individual projects can be given here and thus the interested reader is invited to read their reports which again are only a summary of the entire achievements and much more information can be found in the referenced publications. The structural cooling focus area included results from experimental as well as numerical research on transpiration cooling of thrust chamber structures as well as film cooling supersonic nozzles. The topics of the aft-body flow group reached from studies of classical flow separation to interaction of rocket plumes with nozzle structures for sub-, trans-, and supersonic conditions both experimentally and numerically. Combustion instabilities, boundary layer heat transfer, injection, mixing and combustion under real gas conditions and in particular the investigation of the impact of trans-critical conditions on propellant jet disintegration and the behavior under trans-critical conditions were the subjects dealt with in the combustion chamber focus area. The thrust nozzle group worked on thermal barrier coatings and life prediction methods, investigated cooling channel flows and paid special attention to the clarification and description of fluid-structure-interaction phenomena I nozzle flows. The main emphasis of the focal area thrust-chamber assembly was combustion and heat transfer investigated in various model combustors, on dual-bell nozzle phenomena and on the definition and design of three demonstrations for which the individual projects have contributed according to their research field.

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Investigation of Structured and Unstructured Grid Topology and Resolution Dependence for Scale-Resolving Simulations of Axisymmetric Detaching-Reattaching Shear Layers

Cited by 6 publications

References 10 publications

Numerical Investigation of Space Launch Vehicle Base Flows with Hot Plumes

Numerical Investigation of Space Launch Vehicle Base Flows with Hot Plumes

Sensitivity of scale resolving aft-body flow simulations to numerical model parameter variations

Collaborative Research for Future Space Transportation Systems

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