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Numerical study on the shock transitions during off-design operation of a dual throat thruster

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Abstract

Numerical simulation of the shock transitions during off-design operation of a dual throat nozzle (DTN) is presented. The DTN is a typical passive-altitude-compensation nozzle that exhibits a unique shock transition process during its thrust chambers’ simultaneous operation. The axisymmetric, compressible, turbulent DTN flow field was simulated using a finite-volume Riemann solver based on the advection upstream splitting method. The solution procedure was validated using the experimental wall pressure data reported for a cold flow DTN configuration. The evolution of shock transition from regular reflection to Mach reflection and its reversal was captured. The shock transition hysteresis, its mechanism and control using wall heat transfer were also investigated. Results help improve the off-design operation of the DTN when it is used for a single-stage-to-orbit space mission.

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  1. Department of Aerospace Engineering, Indian Institute of Space Science and Technology, Thiruvananthapuram, India

    S. Jayakrishnan & M. Deepu

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  1. S. Jayakrishnan
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  2. M. Deepu
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Correspondence to M. Deepu.

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Communicated by O. Igra.

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Jayakrishnan, S., Deepu, M. Numerical study on the shock transitions during off-design operation of a dual throat thruster. Shock Waves 31, 929–943 (2021). https://doi.org/10.1007/s00193-021-01037-3

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  • DOI: https://doi.org/10.1007/s00193-021-01037-3

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