Special Issue "Hypersonics: Emerging Research"

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

Deadline for manuscript submissions: 30 September 2021.

Special Issue Editors

Prof. Dr. Sergey Leonov
E-Mail Website
Guest Editor
Department of Aerospace and Mechanical Engineering, College of Engineering, University of Notre Dame, 109 Hessert Lab, Notre Dame, IN 46556, USA
Interests: experimental plasma aerodynamics; weakly ionized plasma generation; flow actuation by electrical discharges; plasma-assisted combustion; diagnostics of low-temperature plasma; hypersonics; aerothermodynamics; high-speed combustion
Prof. Dr. Kojiro Suzuki
E-Mail Website
Guest Editor
Department of Advanced Energy, The University of Tokyo, Tokyo, Japan
Interests: hypersonic high-enthalpy aerothermodynamics; high-speed flying vehicles

Special Issue Information

Dear Colleagues,

This Special Issue is inspired by the broad interests in hypersonics/aerothermodynamics among the aerospace community. Despite a long history of research and development identified in numerous publications, multiple fundamental and engineering aspects are still underexplored and related knowledge not transferred to the technical implementation yet. Hypersonic research is challenging due to an extremely harsh environment associated with atmospheric flight at high speed. This Special Issue is targeting current fundamental research efforts related to hypersonics in a broad range of topics of emerging aerospace applications.

Manuscripts are solicited describing experimental, computational, and/or theoretical research related to hypersonics/aerothermadynamics with a focus on fundamental studies. Publications related to a specific application are relevant to this Special Issue’s scope as well. Submissions may also include ongoing project reports and studies addressing problems in other fields, such as propulsion, energy, or the environment. Topics include but are not limited to:

  • Mach 5 and higher aerodynamics, aerodynamic design, waveriders;
  • Shock waves and shock wave–boundary layer interaction;
  • Hypersonic BL instabilities, laminar-to-turbulent transition;
  • Space transportation system, re-entry, entry to planetary atmosphere;
  • Heat flux control, thermal protection system;
  • Duct-driven high-speed flow control;
  • Ramjet/scramjet flowpath, flameholding, and stability;
  • Thermochemical nonequilibrium flow, rarefied gas dynamics;
  • Magnetohydrodynamics;
  • Ground test facilities, flight experiments;
  • etc.

Prof. Dr. Sergey B Leonov
Prof. Dr. Kojiro Suzuki
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 papers will be 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 1600 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

  • hypersonics
  • aerothermodynamics
  • ramjet
  • scramjet
  • high-speed flow control
  • shock waves

Published Papers (2 papers)

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Research

Article
Numerical Study on Low-Temperature Region as Heat Sink and Its Heat Dissipation Capacity for Hypersonic Vehicle
Aerospace 2021, 8(9), 238; https://doi.org/10.3390/aerospace8090238 - 30 Aug 2021
Viewed by 144
Abstract
Researches have focused on the thermal protection system (TPS) of hypersonic vehicles under severe aerodynamic heat. According to the second law of thermodynamics, heat transfer needs to consume a heat sink, but the cold energy provided by the airborne heat sink is limited. [...] Read more.
Researches have focused on the thermal protection system (TPS) of hypersonic vehicles under severe aerodynamic heat. According to the second law of thermodynamics, heat transfer needs to consume a heat sink, but the cold energy provided by the airborne heat sink is limited. Therefore, it is necessary to explore new available heat sinks during hypersonic cruise. This paper numerically calculated the wall temperature distribution of hypersonic vehicle X-51A with different Mach numbers, altitudes and angles of attack using ANSYS Fluent 19.0. A dimensionless parameter, relative temperature coefficient rt, was proposed to characterize the relative value of local wall temperature in the whole wall temperature range. The distribution regularity and influencing factors of wall temperature were summarized. The low-temperature region which is less affected by flight conditions was divided as the heat sink and its heat dissipation capacity (Q) and characteristics were studied. The angle of attack has great influence on the temperature distribution. In XY view the rear side of leeward surface is least affected by flight conditions and its rt is less than 0.2, which can be used as a low-temperature region. Taking this region as a heat sink to dissipate heat, it is found that the Q of the new heat sink is 30 kW/m2 at Ma 3, 90 kW/m2 at Ma 4 and 200 kW/m2 at Ma 5. The Q increases greatly with the increase in Mach number, and the convective heat transfer coefficient (h) also increases. At the same Q, the h decreases with the increase in Mach number. The exploration of low-temperature region as heat sink has an important reference for reducing the dependence on consumable heat sink and alleviating the energy shortage of the hypersonic vehicle. Full article
(This article belongs to the Special Issue Hypersonics: Emerging Research)
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Article
Global Skewness and Coherence for Hypersonic Shock-Wave/Boundary-Layer Interactions with Pressure-Sensitive Paint
Aerospace 2021, 8(5), 123; https://doi.org/10.3390/aerospace8050123 - 22 Apr 2021
Viewed by 594
Abstract
The global surface pressure was measured on a 7° half-angle circular cone/flare model at a nominally zero angle of attack using pressure-sensitive paint (PSP). These experiments were conducted to illustrate fast PSP’s usefulness and effectiveness at measuring the unsteady structures inherent to [...] Read more.
The global surface pressure was measured on a 7° half-angle circular cone/flare model at a nominally zero angle of attack using pressure-sensitive paint (PSP). These experiments were conducted to illustrate fast PSP’s usefulness and effectiveness at measuring the unsteady structures inherent to hypersonic shock-wave/boundary-layer interactions (SWBLIs). Mean and fluctuating surface pressure was measured with a temperature-corrected, high-frequency-response (≈10 kHz) anodized-aluminum pressure-sensitive paint (AA-PSP) allowing for novel, global calculations of skewness and coherence. These analyses complement traditional SWBLI data-reduction methodologies by providing high-spatial-resolution measurements of the mean and fluctuating locations of the shock feet, as well as the frequency-dependent measure of the relationship between characteristic flow features. The skewness indicated the mean locations of the separation and reattachment shock feet as well as their fluctuations over the course of the test. The coherence indicated that the separation and reattachment shock feet fluctuate about their mean location at the same frequency as one another, but 180 degrees out of phase. This results in a large-scale ‘breathing motion’ of the separated region characteristic of large separation bubbles. These experimental findings validate the usefulness of AA-PSP, and associated data-reduction methodologies, to provide global physical insights of unsteady SWBLI surface behavior in the hypersonic flow regime. Similar methodologies can be incorporated in future experiments to investigate complex and novel SWBLIs. Full article
(This article belongs to the Special Issue Hypersonics: Emerging Research)
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