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

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

doi:10.1007/s12567-021-00400-5

Cited by 3 publications

(2 citation statements)

References 19 publications

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“…Prior to the computations described above, the numerical method was subjected to a validation study based on a similar axisymmetric backward-facing step geometry with centric air jet. A detailed discussion on this work featuring sensitivity studies on numerical model parameters (i. e. time step size, turbulence model, fluid modeling, circumferential grid resolution, filter length definition and the data collection period) is available in Schumann et al (2021b). The definition of the test case was taken from Deprés et al (2004).…”

Section: Iddes Validation Studiesmentioning

confidence: 99%

“…Experimental data from Weiss et al (2009); Deprés et al (2004) and numerical data from Meliga et al (2009) agree well with the results from the presented computational setup. Details on the validation particularly with regard to the RMS pressure coefficient distribution and PSD of wall pressure fluctuations can be found in Schumann et al (2021b).…”

Section: Iddes Validation Studiesmentioning

confidence: 99%

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Plume and wall temperature impact on the subsonic aft-body flow of a generic space launcher geometry

Kirchheck,

Schumann,

Fertig

et al. 2024

Preprint

Self Cite

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Experimental and numerical simulation of launcher base flows is crucial for future launcher design. In experiments, the exhaust plume simulation is often limited to cold or slightly heated gases. In numerical simulations, multi-species reactive flow is often neglected due to limited resources. The impact of these simplifications on the relevant flow features compared to real flight scenarios needs to be characterized in order to enhance the design process. Experimental and numerical investigations were carried out in the frame of the SFB/TRR 40 Collaborative Research Centre in order to study the impact of plume and wall temperature on the base flow of a generic small-scale launcher configuration. Wind tunnel tests were performed in the Hot Plume Testing Facility (HPTF) at DLR Cologne, using subsonic ambient flow and pressurized air or hydrogen-oxygen-combustion as exhaust gases. The tests were numerically rebuilt using the DLR TAU code employing a scale-resolved IDDES approach, including thermal coupling and detailed chemistry. The paper combines the experimental and numerical findings from the SFB/TRR 40 base flow studies and highlights the most prominent influences on the mean flow field, the pressure field, the dynamic wake flow motion and the resulting aerodynamic forces on the nozzle. High-frequency pressure measurements, high-speed Schlieren recordings and time-resolved CFD results are evaluated using spectral and modal analysis of the one- and two-dimensional flow field data.

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Section: Iddes Validation Studiesmentioning

confidence: 99%

Section: Iddes Validation Studiesmentioning

confidence: 99%

Plume and wall temperature impact on the subsonic aft-body flow of a generic space launcher geometry

Kirchheck,

Schumann,

Fertig

et al. 2024

Preprint

Self Cite

View full text Add to dashboard Cite

show abstract

Plume and wall temperature impact on the subsonic aft-body flow of a generic space launcher geometry

Kirchheck,

Schumann,

Fertig

et al. 2024

Exp Fluids

View full text Add to dashboard Cite

Experimental and numerical simulation of launcher base flows are crucial for future launcher design. In experiments, exhaust plume simulation is often limited to cold or slightly heated gases. In numerical simulations, multi-species reactive flow is often neglected due to limited resources. The impact of these simplifications on the relevant flow features, compared to real flight scenarios, needs to be characterized in order to enhance the design process. Experimental and numerical investigations were carried out within the framework of the SFB/TRR 40 Collaborative Research Centre to study the impact of plume and wall temperature on the base flow of a generic small-scale launcher configuration. Wind tunnel tests were performed in the Hot Plume Testing Facility (HPTF) at DLR, Cologne, using subsonic ambient flow and pressurized air or hydrogen–oxygen combustion as exhaust gases. The tests were numerically rebuilt using the DLR TAU code employing a scale-resolved IDDES approach, including thermal coupling and detailed chemistry. The paper combines the experimental and numerical findings from the SFB/TRR 40 base flow studies and highlights the most prominent influences on the mean flow field, the pressure field, the dynamic wake flow motion, and the resulting aerodynamic forces on the nozzle. High-frequency pressure measurements, high-speed schlieren recordings, and time-resolved CFD results are evaluated using spectral and modal analysis of the one- and two-dimensional flow field data.

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Prediction of Wall-Pressure Fluctuations in Channel Flow Using a Hybrid RANS-LES Model with a Wall Function

Lane,

Croaker,

Alenius

et al. 2024

Preprint

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Pressure fluctuations at a surface beneath a turbulent boundary layer are of interest in a wide range of engineering applications as a basis for quantifying vibration and flow noise. Pressure fluctuations can be predicted using Large-Eddy Simulation (LES), but the computational cost of conventional wall-resolved LES is excessive due to the very small mesh spacings required for the inner boundary layer. To reduce the number of mesh cells, wall-modelling techniques may be introduced. In this study, the Improved Delayed Detached Eddy Simulation (IDDES) model was investigated as a wall modelling technique using channel flow as a test case, and its performance was compared with wall-resolved LES and wall-modelling based on a wall function. Previous investigations of IDDES, have typically assessed the accuracy of the method in terms of velocity statistics only. However, predictions of the wall-pressure fluctuations were also assessed in this study. Mesh refinement was investigated as a means to improve accuracy. However, IDDES was also combined with a wall function, allowing coarser wall-normal mesh spacings. With these modifications, the wall-pressure wavenumber and frequency spectra could be predicted fairly accurately over a wide range, for friction velocity Reynolds numbers from 2000 to 8000.

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

Cited by 3 publications

References 19 publications

Plume and wall temperature impact on the subsonic aft-body flow of a generic space launcher geometry

Plume and wall temperature impact on the subsonic aft-body flow of a generic space launcher geometry

Plume and wall temperature impact on the subsonic aft-body flow of a generic space launcher geometry

Prediction of Wall-Pressure Fluctuations in Channel Flow Using a Hybrid RANS-LES Model with a Wall Function

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