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Aerospace
Special Issues
Innovations in Hypersonic Propulsion Systems
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Innovations in Hypersonic Propulsion Systems

A special issue of Aerospace (ISSN 2226-4310). This special issue belongs to the section "Aeronautics".

Deadline for manuscript submissions: closed (15 April 2025) | Viewed by 3004

Special Issue Editors

Prof. Dr. Guoping Huang

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Guest Editor
College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
Interests: high-speed flows; waverider design, intakes design; shock waves; aerodynamics
Dr. Omer Musa

E-Mail
Guest Editor
College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
Interests: ramjets; computational fluid dynamics; combustion; internal waverider Intake; aerodynamics
Special Issues, Collections and Topics in MDPI journals
Dr. Yingkun Li

E-Mail Website
Guest Editor
Key Laboratory of Special Engine Technology, Ministry of Education, School of Mechanic Engineering, Nanjing University of Science and Technology, Nanjing 210094 ,China
Interests: fluid structure interaction; shock wave/boundary layer interaction; supersonic flows; hypersonic flows; panel flutter; overset grid technology; ignition transient; solid rocket motor; dual pulse motor; aerodynamics; flow control; flow separation
Dr. Zonghan Yu

E-Mail Website
Guest Editor
School of Mechanical and Materials Engineering, North China University of Technology, Beijing, China
Interests: aerospace engineering; hypersonic flow; combined cycle propulsion; fluid dynamics; boundary layer diversion

Special Issue Information

Dear Colleagues,

The field of hypersonic propulsion systems is advancing rapidly, driven by the demand for high-speed flight technologies that can achieve velocities greater than five times the speed of sound. Innovations in this area have the potential to revolutionize aerospace engineering, creating new possibilities for both military and civilian applications, including space exploration, defense, and high-speed commercial travel.

We are seeking high-quality papers that explore recent developments, breakthroughs, and innovations in hypersonic propulsion systems. This Special Issue aims to provide a comprehensive overview of the latest theoretical, experimental, and computational research in this dynamic field. Contributions that offer new insights, propose novel technologies, or address existing challenges in hypersonic propulsion are particularly welcome.

Areas of interest for this Special Issue include, but are not limited to, the following:

  • Hypersonic air-breathing engines: design, analysis, and performance optimization;
  • Scramjet and dual-mode ramjet technologies;
  • Materials and structures for hypersonic propulsion systems;
  • Thermal management and cooling techniques for hypersonic vehicles;
  • Combustion processes and fuel efficiency in hypersonic regimes;
  • Shockwave and boundary layer interactions;
  • Advanced propulsion concepts for space and high-altitude applications;
  • Computational fluid dynamics (CFD) methods for hypersonic flows;
  • Experimental methods and facilities for hypersonic testing;
  • Flight testing and validation of hypersonic propulsion systems;
  • Interdisciplinary approaches to hypersonic vehicle design and integration.

We invite researchers and practitioners from academia, industry, and government agencies to contribute their latest findings and join us in advancing the frontiers of hypersonic propulsion technology. Work in related areas is also welcome, as it contributes to the overarching goal of this Special Issue. We encourage submissions that address these topics and other related areas to provide a broad perspective on the current state and future directions of hypersonic propulsion systems.

Prof. Dr. Guoping Huang
Dr. Omer Musa
Dr. Yingkun Li
Dr. Zonghan Yu
Guest Editors

Manuscript Submission Information

Manuscripts should be submitted online at www.mdpi.com by registering and logging in to this website. Once you are registered, click here to go to the submission form. Manuscripts can be submitted until the deadline. All submissions that pass pre-check are peer-reviewed. Accepted papers will be published continuously in the journal (as soon as accepted) and will be listed together on the special issue website. Research articles, review articles as well as short communications are invited. For planned papers, a title and short abstract (about 100 words) can be sent to the Editorial Office for announcement on this website.

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-blind 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.

Please visit the Instructions for Authors page before submitting a manuscript. The Article Processing Charge (APC) for publication in this open access journal is 2400 CHF (Swiss Francs). Submitted papers should be well formatted and use good English. Authors may use MDPI's English editing service prior to publication or during author revisions.

Keywords

  • computational fluid dynamics (CFD)
  • hypersonic propulsion
  • scramjets and dual-mode ramjets intakes
  • rocket-based combined cycle (RBCC)
  • turbine-based combined cycle (TBCC)
  • high-temperature materials
  • thermal management
  • aero-thermodynamics
  • fuel injection and combustion

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Further information on MDPI's Special Issue policies can be found here.

Published Papers (3 papers)

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Research

19 pages, 10628 KiB  
Article
Numerical Analysis of Aerodynamic and Thermal Performance of Streamline Heat Pipe Heat Exchanger Assisted by Fins
by Weicheng Qi, Yuanwei Lyu, Honggang Zeng, Jingyang Zhang and Fenming Wang
Aerospace 2025, 12(3), 163; https://doi.org/10.3390/aerospace12030163 - 20 Feb 2025
Viewed by 580
Abstract
This study numerically explores the feasibility of a streamlined heat pipe heat exchanger in precooling technology in supersonic vehicles. Emphasis has been placed on the role of fins installed in the condensation section in affecting the aerodynamic and thermal characteristics of the streamline [...] Read more.
This study numerically explores the feasibility of a streamlined heat pipe heat exchanger in precooling technology in supersonic vehicles. Emphasis has been placed on the role of fins installed in the condensation section in affecting the aerodynamic and thermal characteristics of the streamline heat pipe heat exchanger. The results show that the installation of fins in the condensation section effectively improved the overall heat transfer capacity of the streamline heat pipe heat exchanger. The temperature drop with fins is up to 685 K, which is 20 K larger than the case without fins. Simultaneously, fins resulted in 6.4% and 25.4% increases in the pressure loss coefficient in the evaporation and condensation section compared to the case without fins. The aerodynamic and thermal characteristics are closely related to the mass flow rate of intake air and kerosene (RP-3). The pressure drop and temperature drop are positively related to the mass flow rate of RP-3. In contrast, as the qa increases, the heat exchange per qa decreases, and the temperature of the air outlet of the evaporation section increases correspondingly. In the evaporation section, as the qRP-3 increases, the temperature drop in the condensation section first increases and then remains unchanged, and its pressure loss coefficient decreases. The temperature drop in the intake air is positive and related to the qRP-3. The results obtained in this study are significant because they can provide technical support in the high performance of heat exchangers. Full article
(This article belongs to the Special Issue Innovations in Hypersonic Propulsion Systems)
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18 pages, 13315 KiB  
Article
Numerical Investigation of the Coupling Effects of Pulsed H2 Jets and Nanosecond-Pulsed Actuation in Supersonic Crossflow
by Keyu Li and Jiangfeng Wang
Aerospace 2025, 12(1), 44; https://doi.org/10.3390/aerospace12010044 - 11 Jan 2025
Viewed by 793
Abstract
Numerical investigations were conducted to analyze the coupling effects of pulsed H2 jets and nanosecond-pulsed actuation (NS-SDBD) in a supersonic crossflow. The FVM was employed to solve the multi-component 2D URANS equations with the SST k-omega turbulence model, while H2-air [...] Read more.
Numerical investigations were conducted to analyze the coupling effects of pulsed H2 jets and nanosecond-pulsed actuation (NS-SDBD) in a supersonic crossflow. The FVM was employed to solve the multi-component 2D URANS equations with the SST k-omega turbulence model, while H2-air combustion was described using a seven species–seven reactions chain reaction model, and the plasma thermal effect was represented by a phenomenological model. The backward-facing step flows with an inlet Mach number of 2.5 and a pulsed jet frequency of 10 kHz under different actuation conditions were simulated. The combustion enhancement mechanism under an actuation frequency of 20 kHz was analyzed. Research indicates that compression waves induced by NS-SDBD enhance H2-air mixing and facilitate temperature transport as the flow progresses. This progress is significantly associated with the flow structures generated by pulsed jets. Under this condition, the fuel utilization rate in the flow field increased by 61.2%, the total pressure recovery coefficient increased by 5.34%, and the outlet total temperature slightly increased even with a 50% reduction in fuel flow rate. Comparative analysis of different actuation cases demonstrates that evenly distributed actuation within the jet cycle yields better effects. The innovation of this study lies in proposing and exploring a potential method to address inadequate combustion under high-speed inflow conditions, which couples NS-SDBD with pulsed hydrogen jets. Full article
(This article belongs to the Special Issue Innovations in Hypersonic Propulsion Systems)
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23 pages, 12326 KiB  
Article
Research on the Criteria for Determining the Starting Performance of an Inward-Turning Inlet by Integrating the Concept of the Equivalent Contraction Ratio
by Fanshuo Meng, Bo Jin, Xiaolong He, Zheng Chen, Wenhui Yan, Zhenjun Zhao and Zonghan Yu
Aerospace 2024, 11(11), 941; https://doi.org/10.3390/aerospace11110941 - 13 Nov 2024
Viewed by 1059
Abstract
The prediction of hypersonic inlet starting performance is crucial for the successful ignition of the combustion chamber, directly impacting the overall performance of the propulsion system. This challenge arises especially when freestream conditions vary. Therefore, this paper proposes the concept of the equivalent [...] Read more.
The prediction of hypersonic inlet starting performance is crucial for the successful ignition of the combustion chamber, directly impacting the overall performance of the propulsion system. This challenge arises especially when freestream conditions vary. Therefore, this paper proposes the concept of the equivalent contraction ratio, and establishes and analyzes the intrinsic correlation between the geometric contraction ratio and angle of attack on the starting performance of three-dimensional inward-turning inlet. The results indicate the following: (1) The startability index can be applied to determine the start boundary of the three-dimensional inward-turning inlet under conditions of the freestream Mach number of 6.0 and an altitude of 27 km, with a deviation of no more than 6.6% from the optimal SI = 0.087 criterion; (2) The start boundary after applying the equivalent contraction ratio shows deviations not exceeding 4.0% under positive angle-of-attack conditions compared to the startability index, while the deviation is larger under negative angle-of-attack conditions, reaching a maximum of 13.3%. After applying a correction formula, the deviations can be reduced to within 2.0%; (3) For the same equivalent contraction ratio, the differences in starting performance between different positive and negative angle-of-attack conditions may fundamentally arise from the degree of compression of the inlet. Finally, the equivalent contraction ratio theory is proven to be able to quickly and easily predict the accurate starting performance of the inward-turning inlet at different angles of attack, improving the breadth and efficiency of engineering predictions. Full article
(This article belongs to the Special Issue Innovations in Hypersonic Propulsion Systems)
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