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Screech-tone prediction using upstream-travelling jet modes

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Abstract

The purpose of this paper is to characterise and model the A1 and A2 screech modes in supersonic jets operating at off-design conditions. The usual screech-modelling scenario involves a feedback loop between a downstream-travelling Kelvin–Helmholtz instability wave and an upstream-travelling acoustic wave. We review state-of-the-art screech-frequency prediction models and associated limitations. Following the work of Edgington-Mitchell et al. (J Fluid Mech 855, 2018), a new prediction approach is proposed where the feedback loop is closed by the upstream-travelling jet modes first discussed in Tam and Hu (J Fluid Mech 201:447–483, 1989) in lieu of the free-stream sound waves. The Kelvin–Helmholtz and upstream-travelling jet modes are obtained using a cylindrical vortex-sheet model. The predictions provide a better agreement with experimental observations than does the classical screech-prediction approach. Screech dynamics associated with the staging process is explored through a wavelet analysis, highlighting that staging involves mutually exclusive switching that is underpinned by non-linear interactions.

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Acknowledgements

M. M. acknowledges the support of Centre National d’Études Spatiales (CNES) under a post-doctoral grant.

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Authors and Affiliations

  1. Département Fluides Thermique et Combustion, Institut Pprime-CNRS-Université de Poitiers-ENSMA, 11 Boulevard Marie et Pierre Curie, 86962, Chasseneuil-du-Poitou, Poitiers, France

    Matteo Mancinelli, Vincent Jaunet & Peter Jordan

  2. Direction des Lanceurs, CNES, 52 rue Jacques Hillairet, 75612, Paris, France

    Matteo Mancinelli

  3. Department of Mechanical Engineering, University of Michigan, 2350 Hayward Street, Ann Arbor, MI, 48109, USA

    Aaron Towne

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  1. Matteo Mancinelli
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  2. Vincent Jaunet
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  3. Peter Jordan
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  4. Aaron Towne
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Correspondence to Matteo Mancinelli.

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Appendix 1: Far-field measurements

Appendix 1: Far-field measurements

Pressure measurements were performed in the far field to verify that the screech dynamics of modes A1 and A2 was not affected by the close positioning of the near-field microphone array with respect to the nozzle. The far-field microphone was placed at a radial distance \(r/D\approx 90\) at a polar position \(\psi =120^\circ\), with the polar angle measured from the downstream axis of the jet. A coarser jet Mach-number resolution \(\varDelta M_{\text {j}}=0.01\) was used to carry out the far-field experimental tests.

Figure 9 shows the spectral contour map for all \(M_{\text {j}}\). As for the near-field measurements, we restrict the attention on the frequency band where modes A1 and A2 live. The signature of the two modes is the same one arising in the near field and shown in Figs. 4 and 5. Hence, the close positioning of the microphone array in the near field has no effects on the emergence of the axisymmetric screech modes.

Fig. 9
figure 9

Spectral contour map of the far-field microphone at the polar position \(\psi =120^\circ\)

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Mancinelli, M., Jaunet, V., Jordan, P. et al. Screech-tone prediction using upstream-travelling jet modes. Exp Fluids 60, 22 (2019). https://doi.org/10.1007/s00348-018-2673-2

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