Transverse injection into Mach 2 flow behind a rearward-facing step - A 3-D, compressible flow test case for hypersonic combustor CFD validation

McDaniel, James C.; Fletcher, Douglas G.; Hartfield, Roy J.; Hollo, Steven D.

doi:10.2514/6.1991-5071

Cited by 42 publications

(60 citation statements)

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“…The calculation physical model is chosen corresponding to the experiment as discussed by McDaniel et al [21]. Detailed measurements of flow parameters in the experiment were carried out using laser-induced iodine fluorescence (LIIF) and planar laser-induced iodine fluorescence (PLIIF) techniques.…”

Section: Resultsmentioning

confidence: 99%

“…The reattachment point is determined where the surface velocity is zero and the reattachment length is defined as the length between the step corner and the reattachment point. Typically, both experimental and numerical studies in the past mainly focus on the low Mach number conditions [17,18,21,25,31]. However, with the hypersonic aircrafts being developed, the investigations of sudden expansion flow in high Mach number conditions such as the airfoil problem have become increasingly important.…”

Section: Effect Of Inflow Mach Number On Reattachmentmentioning

confidence: 99%

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Effects of Inflow Mach Number and Step Height on Supersonic Flows over a Backward-Facing Step

Liu

Wang

Guo

et al. 2013

Advances in Mechanical Engineering

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The backward-facing step is practically implicated in many devices, encountering the massive separation flows. In the present study, simulations of supersonic flow over a backward-facing step have been carried out employing both RANS and LES. The simulated results are validated against the experimental data. The results of RANS and LES show a good comparison with the experimental results. Different inflow Mach numbers and expansion ratios are also investigated. The reattachment length decreases with the increase of inflow Mach number. The duct height has a great effect on the flow patterns. The present conclusions are helpful to understand the physics in supersonic separation flows and also provide theory basis for engineering applications.

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Section: Resultsmentioning

confidence: 99%

Section: Effect Of Inflow Mach Number On Reattachmentmentioning

confidence: 99%

Effects of Inflow Mach Number and Step Height on Supersonic Flows over a Backward-Facing Step

Liu

Wang

Guo

et al. 2013

Advances in Mechanical Engineering

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“…Two sets of calculations were carried out for with and without transverse injection and qualitative behaviour of the flow has been analysed and the quantitative comparisons has been made for various flow profiles at different axial stations by comparing with experimental results 10 and other numerical calculations 20,21 .…”

Section: Resultsmentioning

confidence: 99%

“…Recirculation bubble downstream of the step is captured crisply in the simulation. The length of the recirculation bubble is about 5 D. The non-dimensionalised pressure profiles at combustor mid-plane have been compared with experimental results 10 and the computational results of Manna and Chakraborty 21 in Fig. 6 for different axial stations x/D = 2.05, 0, and 6.05.…”

Section: Flow Field Without Injection Casementioning

confidence: 99%

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Numerical Exploration of Staged Transverse Injection into Confined Supersonic

Sriram¹,

Chakraborty²

2011

DSJ

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Staged transverse sonic injection into supersonic flow in a confined environment usually employed in scramjet combustor has been explored numerically using an indigenously developed three-dimensional Reynolds Averaged Navier Stokes solver with Roes scheme and k-w turbulence model. Simulations were carried out for both without injection and with injection in Mach 2 flow behind a backward-facing step in a rectangular duct. Simulation captured all finer details of flow structures including recirculation bubble behind a backward-facing step, barrel shocks and Mach discs caused due to transverse injection and reattachment of shear layer in the downstream wake region. K-w turbulence model with compressibility correction performed extremely well in predicting the overall behaviour of the flow field. The jet from the second injector was found to penetrate more in the free-stream due to the loss of free-stream total pressure across the barrel shock of the first injection point. Excellent agreement of computed profiles of various flow parameters at different axial locations in the duct with experimental results and other numerical results available in the literature demonstrate the robustness and accuracy of the indigenously developed code.

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Suitability of the k–ω turbulence model for scramjet flowfield simulations

Chan

Jacobs

Mee

2011

Numerical Methods in Fluids

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SUMMARY The suitability of Wilcox's 2006 k– ω turbulence model for scramjet flowfield simulations is demonstrated by validation against five test cases that have flowfields representative of those to be expected in scramjets. The five test cases include a 2D flat plate, an axisymmetric cylinder, a backward‐facing step, the mixing of a pair of coaxial jets and the interaction between a shock wave and turbulent boundary layer. A generally good agreement between the numerical and experimental results is obtained for all test cases. These tests reveal that despite the turbulence model's sensitivity to freestream turbulence properties, the numerically predicted skin friction agrees with experimental data and theoretical correlations to their degree of uncertainty. The tests also confirm the importance of using a y+ value of less than 1 in getting accurate surface heat transfer distributions. In the coaxial jets case, the importance of matching the turbulence intensities at the inflow plane in improving the predictions of the turbulent mixing phenomena is also shown. A review of guidelines with regard to the setting up of grids and specification of freestream turbulence properties for turbulent Reynolds‐averaged Navier–Stokes CFD simulations is also included in this paper. Copyright © 2011 John Wiley & Sons, Ltd.

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Transverse injection into Mach 2 flow behind a rearward-facing step - A 3-D, compressible flow test case for hypersonic combustor CFD validation

Cited by 42 publications

References 0 publications

Effects of Inflow Mach Number and Step Height on Supersonic Flows over a Backward-Facing Step

Effects of Inflow Mach Number and Step Height on Supersonic Flows over a Backward-Facing Step

Numerical Exploration of Staged Transverse Injection into Confined Supersonic

Suitability of the k–ω turbulence model for scramjet flowfield simulations

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