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Aerospace
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Flight at Supersonic and Hypersonic Velocities: Aerodynamics, Flow Control, Propulsion
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Flight at Supersonic and Hypersonic Velocities: Aerodynamics, Flow Control, Propulsion

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

Deadline for manuscript submissions: 15 February 2025 | Viewed by 2609

Special Issue Editor

Dr. Konstantin Volkov

E-Mail Website
Guest Editor
Department of Mechanical Engineering, School of Engineering, Faculty of Engineering, Computing and The Environment, Kingston University London, Roehampton Vale Campus, Friars Avenue, London SW15 3DW, UK
Interests: aerospace engineering; aerodynamics; computational fluid dynamics; high-speed flow; multiphase flow
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

The complexity of various technical problems associated with the design and development of supersonic and hypersonic vehicles and related systems leads to the need for research in the field of aerodynamics, flow control, and propulsion using mathematical modelling and experimental tools.

Supersonic and hypersonic vehicles could enable a range of future aviation and space missions. However, the extreme environmental conditions associated with high-Mach-number flight and temperatures pose a major challenge for supersonic and hypersonic vehicle aerodynamics, flight control, and propulsion systems. Structural components are at risk of damage under such critical flow conditions, since they can resonate and endure vibrational fatigue. In the supersonic and hypersonic regime, thermal loads become an additional concern due to the extreme aerodynamic heating, thereby posing stringent requirements on the material selection and thermal protection system.

The complexity of high-Mach-number vehicles, however, requires the closer coupling of aerodynamics and design principles with the development of new flight control and propulsion systems to achieve expanded levels of performance and structural durability. This Special Issue focuses on the synthesis of fundamental disciplines and practical applications involved in the investigation, description, and analysis of supersonic and hypersonic aircraft flight, including applied aerodynamics, aircraft propulsion, flight control, and related topics.

A particular focus of this Special Issue is the development of theoretical, computational, and experimental methods in supersonic and hypersonic aerodynamics and hybrid ramjet/scramjet propulsion systems. Computational methods are widely used by the practicing aerodynamicist, and this Special Issue covers techniques used to improve understanding of the physical models that underlie computational methods.

Dr. Konstantin Volkov
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

  • supersonic flow
  • hypersonic flow
  • aerodynamics
  • flow control
  • propulsion
  • shock wave
  • heat transfer
  • shape optimisation
  • thermal protection
  • scramjet
  • ramjet

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Published Papers (3 papers)

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Research

17 pages, 7427 KiB  
Article
Effects of the Fuel Species on the Combustion Pressure in a Two Staged Fueled Scramjet Combustor
by Hironobu Nishiguchi, Masatoshi Kodera and Sadatake Tomioka
Aerospace 2025, 12(1), 66; https://doi.org/10.3390/aerospace12010066 - 18 Jan 2025
Viewed by 343
Abstract
Two-staged fuel injection configuration for scramjet combustors has been shown to be effective in distributing heat release in the combustor for preventing the unstart transition of the engine by suppressing peak pressure while increasing the pressure thrust. In this study, the effect of [...] Read more.
Two-staged fuel injection configuration for scramjet combustors has been shown to be effective in distributing heat release in the combustor for preventing the unstart transition of the engine by suppressing peak pressure while increasing the pressure thrust. In this study, the effect of fuel species on combustion characteristics in a two-staged fueled scramjet combustor was investigated. Wall pressure measurements in a two-staged fueled scramjet combustor were conducted in a combustion wind tunnel facility with fuels having different reactivity, such as H2 and CH4. Reynolds-Averaged Navier–Stokes/Large Eddy Simulation (RANS/LES) hybrid simulations were performed to verify the interaction characteristics between the primary and secondary combustion zones for different fuels. The experimental results confirmed that pressure peaks at injections were clearly separated in the hydrogen case, while these interacted with each other in the methane case with a lower reactivity than H2. The RANS/LES Hybrid analysis predicted this effect of fuel reactivity on the pressure distribution, namely, the heat release delay of the first stage fuel caused the interaction with the second stage fuel heat release. The results indicate that the need to design the staged fueled combustor, i.e., the injection stage interval accordingly to the reactivity of the fuel. Full article
(This article belongs to the Special Issue Flight at Supersonic and Hypersonic Velocities: Aerodynamics, Flow Control, Propulsion)
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14 pages, 286 KiB  
Article
Interaction of a Dense Layer of Solid Particles with a Shock Wave Propagating in a Tube
by Konstantin Volkov
Aerospace 2024, 11(10), 850; https://doi.org/10.3390/aerospace11100850 - 15 Oct 2024
Viewed by 697
Abstract
A numerical simulation of an unsteady gas flow containing inert solid particles in a shock tube is carried out using the interpenetrating continuum model. The gas and dispersed phases are characterized by governing equations that express the concepts of mass, momentum, and energy [...] Read more.
A numerical simulation of an unsteady gas flow containing inert solid particles in a shock tube is carried out using the interpenetrating continuum model. The gas and dispersed phases are characterized by governing equations that express the concepts of mass, momentum, and energy conservation as well as an equation that shows the change of the volume fraction of the dispersed phase. Using a Godunov-type approach, the hyperbolic governing equations are solved numerically with an increased order of accuracy. The working section of the shock tube containing air and solid particles of various sizes is considered. The shock wave structure is discussed and computational results provide the spatial and temporal dependencies of the particle concentration and other flow quantities. The numerical simulation results are compared with available experimental and computational data. Full article
(This article belongs to the Special Issue Flight at Supersonic and Hypersonic Velocities: Aerodynamics, Flow Control, Propulsion)
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32 pages, 31602 KiB  
Article
The Impact of Upstream Static Deformation on Flow Past a Cylinder/Flare
by Aaron Becks, Tyler Korenyi-Both, Jack J. McNamara and Datta V. Gaitonde
Aerospace 2024, 11(5), 412; https://doi.org/10.3390/aerospace11050412 - 20 May 2024
Viewed by 1055
Abstract
Reynolds-averaged Navier–Stokes simulations are performed for supersonic turbulent flow over a cylinder/flare with upstream surface distortion representative of structural deformation induced via fluid–structural and fluid–thermal–structural behavior. Broad parametric analysis is carried out through the generation of Kriging-response surfaces from a database of general [...] Read more.
Reynolds-averaged Navier–Stokes simulations are performed for supersonic turbulent flow over a cylinder/flare with upstream surface distortion representative of structural deformation induced via fluid–structural and fluid–thermal–structural behavior. Broad parametric analysis is carried out through the generation of Kriging-response surfaces from a database of general simulations. A posteriori simulations are then carried out at parametric combinations that correspond to extrema in the Kriging response surfaces to gain deeper insights into the interaction between the surface distortion and flow responses. Upstream distortions tend to decrease, rather than increase, the peak pressure and heat flux loads on the flare compared to an undeformed cylinder. Furthermore, decreases in these quantities reach up to O(10%) compared to up to O(1%) for increases. Integrated quantities over the flare are relatively insensitive to upstream distortion. The corner separation length is the most sensitive quantity to upstream distortion, with protrusions tending to increase the separation length and recessions reducing the separation length. Modifications in the separation length of up to 40% are observed. Reductions in peak loads tend to correspond to increases in the corner separation length. The movement of the surface distortion relative to the corner indicates a negligible impact beyond 1.5 distortion lengths from the corner, and the largest impact on the corner separation length occurs when distortion is directly adjacent. These results are an important step toward understanding and quantifying the impact of surface deformations on downstream components. Full article
(This article belongs to the Special Issue Flight at Supersonic and Hypersonic Velocities: Aerodynamics, Flow Control, Propulsion)
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