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Aerospace
Special Issues
Combustion and Flow in Propulsion Systems
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Combustion and Flow in Propulsion Systems

A special issue of Aerospace (ISSN 2226-4310). This special issue belongs to the section "Astronautics & Space Science".

Deadline for manuscript submissions: 30 September 2026 | Viewed by 558

Editor

Prof. Dr. Huiqiang Zhang

E-Mail Website
Guest Editor
School of Aerospace Engineering, Tsinghua University, Beijing 100084, China
Interests: combustion instability; breakup and atomization of liquid jet (sheet); modeling of turbulent two-phase reacting flow; high-fidelity numerical simulation for combustion chamber in propulsion system; advanced propulsion

Special Issue Information

Dear Colleagues,

In the present and foreseeable future, aerospace propulsion is still characterized by the combustion-based energy and flow-based injection. Combustion and flow processes are therefore crucial to the propulsion systems not only for their reliable work but also for their high performance. In current widely used propulsion systems, describing, understanding and predicting the processes of the breakup of liquid-fuel (propellant) jet (sheet), stable combustion, ignition and stable combustion limits, as well as combustion instability, still remain challenging issues.

Developing an advanced propulsion system is an eternal pursuit, and there are currently four main directions for such developments that are tightly related to combustion. One is the high-performance propulsion system, which is heavily dependent on combustion under extreme conditions like lean-premixed combustion, supersonic combustion, high-pressure combustion as well as wide-limit combustion for high-temperature rise. The second is the combined-cycle propulsion system in which combustion with collaborative configurations for multi-mode engines are key issues. The third is a new-type propulsion system related to constant-volume combustion, in which stable and self-sustaining detonation and oblique detonation are dominant processes. The last is new-fueled (propellant) propulsion, such as LOx/CH4 and NOFBX for rocket engines, as well as hydrogen and ammonia for gas turbine engines.

In order to promote research on combustion in new and high-performance propulsion systems, this Special Issue is seeking to gather related research findings for efficient communication and dissemination. We look forward to your contributions.

Prof. Dr. Huiqiang Zhang
Guest Editor

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Submitted manuscripts should not have been published previously, nor be under consideration for publication elsewhere (except conference proceedings papers). All manuscripts are thoroughly refereed through a single-anonymized peer-review process. A guide for authors and other relevant information for submission of manuscripts is available on the Instructions for Authors page. Aerospace is an international peer-reviewed open access monthly journal published by MDPI.

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Keywords

  • primary breakup of liquid jet (sheet)
  • stable combustion
  • limits of ignition and stable combustion
  • combustion instability
  • combustion under extreme conditions
  • detonation
  • oblique detonation
  • combustion with collaborative configuration
  • new-fueled combustion (e.g., LOx/CH4, NOFBX, H2, NH3)

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Published Papers (1 paper)

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Research

34 pages, 8273 KB  
Article
Transient Flow Dynamics and Stability of ISRR Inlet During Mode Transition with Dual-Boundary Dynamic Opening: Experiments, CFD, and Stability Window Analysis
by Shilin Yang, Hongliang Qi and Wenyan Song
Aerospace 2026, 13(5), 472; https://doi.org/10.3390/aerospace13050472 - 16 May 2026
Viewed by 308
Abstract
The transient mechanism of dual-boundary dynamic opening in the inlet during stage transition of an integral solid rocket ramjet (ISRR) remains insufficiently understood. To address this issue, a combined approach involving numerical simulations and free-jet experiments was employed. A parametric model describing the [...] Read more.
The transient mechanism of dual-boundary dynamic opening in the inlet during stage transition of an integral solid rocket ramjet (ISRR) remains insufficiently understood. To address this issue, a combined approach involving numerical simulations and free-jet experiments was employed. A parametric model describing the time-sequenced opening of inlet and outlet cover was established. The influences of sequence and progression of opening and flight conditions on transient flow evolution and inlet stability were systematically examined. It is found that when the inlet is opened first, a “dead cavity” tends to form inside the inlet, which subsequently triggers pronounced pressure oscillations. Under baseline conditions, the peak outlet pressure reaches approximately 0.90 MPa, with a dominant frequency of about 66.7 Hz. Conversely, when the outlet is opened first, the cavity-induced oscillation is effectively suppressed; however, a transient “flow choking” overpressure and a delayed establishment of the flow field are observed. The discrepancies between simulations and experiments for key pressure characteristics under two representative opening modes are maintained within 5%, confirming the robustness of the proposed methodology. Further analysis reveals that increasing the Mach number markedly intensifies flow instability and reduces the stability margin, whereas higher flight altitudes help attenuate cavity oscillations. A strong coupling between the opening rate and temporal sequence is also identified. Specifically, for inlet-first scenarios, a slower inlet opening combined with a rapid outlet opening is preferable, while for outlet-first cases, rapid opening on both sides yields better performance. On this basis, a “stability window map” defined by the temporal difference (Δt) and opening duration (Topen) is proposed. This map delineates the distributions of stable, transitional, and hazardous regimes under varying conditions, which may offer a quantitative reference for adaptive control strategies in the ISRR stage of transition. Interestingly, these findings suggest that slight timing adjustments could substantially reshape the transient flow behavior. Notably, the introduction of the dual-boundary temporally coordinated forcing leads to flow responses within the inlet that exhibits pronounced path dependence and non-uniqueness. Such behavior deviates from the conventional understanding established under the single-boundary frameworks, where transient mode-transition processes were typically assumed to be uniquely determined. More importantly, these findings offer a renewed physical interpretation of inlet mode-transition dynamics, thereby providing both quantitative support and practical guidance for the adaptive design of ISRR transition control strategies. In particular, the results suggest that incorporating multi-boundary temporal effects could significantly enhance the robustness and flexibility of the control-law formulation. Full article
(This article belongs to the Special Issue Combustion and Flow in Propulsion Systems)
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