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Aerospace
Special Issues
Recent Advances in Ramjets
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Recent Advances in Ramjets

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

Deadline for manuscript submissions: closed (30 November 2023) | Viewed by 5600

Special Issue Editor

Dr. Omer Musa

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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

Special Issue Information

Dear Colleagues,

Ramjet technology has a long history, but it has also seen a resurgence of interest and activity in recent years due to its potential applications in various fields, such as in the design of missiles, artillery shells, hypersonic vehicles and space launchers. Ramjets are jet engines that use air compression, derived from their forward motion, to generate thrust without using major moving parts. Working best at supersonic speeds, the ramjet engine is one of the most promising propulsion systems for the realization of supersonic and hypersonic flights using subsonic (ramjet) and supersonic (scramjet) combustion. Additionally, they offer continuous thrust at high speeds, increase range and manoeuvrability, reduce weight and cost, and enable new capabilities and missions. However, ramjet technology poses many challenges and limitations, such as ignition, combustion stability, heat management, aerodynamics, materials, integration and control. To address these challenges and harness the benefits of ramjet technology, intensive research and development efforts are required, both from academia and industry. This Special Issue aims to showcase the latest advances in the field of ramjet technology from leading researchers, engineers and scientists.

The papers in this Special Issue cover various topics related to ramjets, including the design principles and analysis of ramjets, experimental techniques, testing methodologies and facilities, computational fluid dynamics (CFD) simulations and models, novel concepts and innovations for ramjet applications, case studies and examples of ramjet systems, and various applications of ramjet engines in hypersonic flight and missile propulsion. We hope this Special Issue will provide a comprehensive overview of the current state of the art in ramjet technology and stimulate new ideas and directions for future research.

Dr. Omer Musa
Guest Editor

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
  • aerodynamics
  • high-speed flow
  • fluid–structure interaction
  • airbreathing jet engines
  • self-sustaining combustion
  • missile defense
  • turbine-based combined cycle

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Published Papers (3 papers)

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Research

19 pages, 8265 KiB  
Article
Contribution of Different Parameters on Film Cooling Efficiency Based on the Improved Orthogonal Experiment Method
by Xinlei Duan, Jianlong Chang, Guangsong Chen, Taisu Liu and He Ma
Aerospace 2024, 11(1), 67; https://doi.org/10.3390/aerospace11010067 - 10 Jan 2024
Cited by 2 | Viewed by 1422
Abstract
The use of film cooling technology is one of the most effective ways to minimize the damage to wall materials caused by the high-temperature environment in a ramjet. Optimization of the design to achieve the highest film cooling efficiency on the hot wall [...] Read more.
The use of film cooling technology is one of the most effective ways to minimize the damage to wall materials caused by the high-temperature environment in a ramjet. Optimization of the design to achieve the highest film cooling efficiency on the hot wall is the focus of current research. Due to the large number of parameters affecting the film cooling efficiency and the interactions between them, an improved orthogonal design-of-experiments method is chosen to investigate the contribution of different parameters. Flat plate film cooling and transverse groove film cooling are simulated numerically. The results indicated that the contribution of each parameter is ranked as hole spacing (S/D) > incidence angle > blowing ratio for flat plate film cooling; hole spacing > transverse groove depth > blowing ratio > incidence angle for transverse groove film cooling. The film cooling efficiency is inversely proportional to the size of the flow field area affected by the vortex ring and directly proportional to the size of the vortex intensity. Transverse groove film cooling forms a more complete film in most cases, which is better than flat plate film cooling. Within the scope of this study, a complete film at S/D > 2.0 cannot be generated on the flat plate, which should not be used in ramjet. Full article
(This article belongs to the Special Issue Recent Advances in Ramjets)
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42 pages, 40684 KiB  
Article
Investigations of the Atomization Characteristics and Mechanisms of Liquid Jets in Supersonic Crossflow
by Donglong Zhou, Jianlong Chang and Huawei Shan
Aerospace 2023, 10(12), 995; https://doi.org/10.3390/aerospace10120995 - 27 Nov 2023
Viewed by 1385
Abstract
In the combustion chamber of scramjets, fuel jets interact with supersonic airflow in the form of a liquid jet in crossflow (LJIC). It is difficult to achieve adequate jet–crossflow mixing and the efficient combustion of fuel in an instant. Large eddy simulation (LES), [...] Read more.
In the combustion chamber of scramjets, fuel jets interact with supersonic airflow in the form of a liquid jet in crossflow (LJIC). It is difficult to achieve adequate jet–crossflow mixing and the efficient combustion of fuel in an instant. Large eddy simulation (LES), the coupled level-set and volume of fluid (CLSVOF) method, and an adaptive mesh refinement (AMR) framework are used to simulate supersonic LJICs in this article. This way, LJIC atomization characteristics and mechanisms can be further explored and analyzed in detail. It is found that the surface waves of the liquid column exist in a two-dimensional form, including vertical and spanwise directions. Column breakup occurs when all the spanwise surface waves between adjacent vertical surface waves break up. Bow shock waves, composed of multiple connected arcuate shock waves, are dynamic and will change with the evolution of the liquid column. The vortex ring movement of supersonic LJICs, whose trends in the vertical and spanwise directions are different, is relatively complex, which is due to the complex and time-dependent shape of liquid columns. Full article
(This article belongs to the Special Issue Recent Advances in Ramjets)
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18 pages, 8947 KiB  
Article
Numerical Study on the Aerodynamic Heating Characteristics of the Cantilevered Injection System for Oblique Detonation Engine Inlets
by Fan Yang, Mingyue Lin, Zongmin Hu and Guilai Han
Aerospace 2023, 10(10), 897; https://doi.org/10.3390/aerospace10100897 - 20 Oct 2023
Viewed by 1464
Abstract
This paper investigates the flowfield patterns and distributions of surface heat flux of the cantilevered injection system for oblique detonation engine inlets. Three-dimensional complex shock wave/boundary layer interaction and shock wave/shock wave interaction between injectors are studied by solving Navier–Stokes equations under laminar [...] Read more.
This paper investigates the flowfield patterns and distributions of surface heat flux of the cantilevered injection system for oblique detonation engine inlets. Three-dimensional complex shock wave/boundary layer interaction and shock wave/shock wave interaction between injectors are studied by solving Navier–Stokes equations under laminar flow conditions. The results indicate that there are three possible positions of localized peak heat flux, i.e., the leading edge of the injector near the bottom, the inlet wall surface below the injector, and the downstream of the injector sidewall. All the regions of high heat flux are related to flow reattachment or stagnation. Three types of flow patterns are observed along the inlet surface, i.e., partial separation, completely regular separation, and completely nonregular separation, resulting in increasingly complex distributions of heat flux. The localized peak heat flux which appears at the leading edge and the sidewalls of the injectors can reach values dozens of times higher than the undisturbed region within the interaction region. Full article
(This article belongs to the Special Issue Recent Advances in Ramjets)
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