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Applied Sciences
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Advances in Hypersonic Flows
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Advances in Hypersonic Flows

A special issue of Applied Sciences (ISSN 2076-3417). This special issue belongs to the section "Aerospace Science and Engineering".

Deadline for manuscript submissions: closed (30 June 2024) | Viewed by 3692

Special Issue Editor

Dr. Jiaao Hao

E-Mail Website
Guest Editor
Department of Aeronautical and Aviation Engineering, The Hong Kong Polytechnic University, Kowloon 999077, Hong Kong
Interests: hypersonic flows; flow stability; computational fluid dynamics

Special Issue Information

Dear Colleagues,

Hypersonic flows typically refer to flows where the Mach number is greater than five. Characterized by high speeds and high temperatures, hypersonic flows involve various flow phenomena that remain to be fully understood. In this Special Issue, we invite submissions addressing, but not limited to, hypersonic transition, shock wave–boundary layer interactions, thermochemical nonequilibrium flows, hypersonic propulsion systems, and hypersonic rarefied flows.

Dr. Jiaao Hao
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. Applied Sciences is an international peer-reviewed open access semimonthly 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

  • hypersonic flows
  • hypersonic aerodynamics
  • hypersonic aerothermodynamics
  • hypersonic rarefied flows

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Published Papers (2 papers)

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Research

18 pages, 20687 KiB  
Article
Investigation of the Inverse Magnus Effect on a Rotating Sphere in Hypersonic Rarefied Flow
by Yazhong Jiang, Yuxing Ling and Shikang Zhang
Appl. Sci. 2024, 14(3), 1042; https://doi.org/10.3390/app14031042 - 25 Jan 2024
Cited by 1 | Viewed by 1221
Abstract
Explorations involving long-endurance and maneuvering flights in the upper atmosphere, as well as research on atmospheric entries of space debris or asteroids, call for a full understanding of hypersonic rarefied flows. The inverse Magnus effect occurs in the hypersonic rarefied flow past a [...] Read more.
Explorations involving long-endurance and maneuvering flights in the upper atmosphere, as well as research on atmospheric entries of space debris or asteroids, call for a full understanding of hypersonic rarefied flows. The inverse Magnus effect occurs in the hypersonic rarefied flow past a rotating sphere, but the aerodynamic behavior is contrary to the Magnus effect in the continuum flow regime. In this article, a series of such flows are numerically studied using the direct simulation Monte Carlo (DSMC) method. By analyzing the flow fields, as well as the distributions of pressure and shear stress on the sphere, the formation of the inverse Magnus force can be attributed to the tangential momentum transfer between incident gas molecules and the windward surface. The variation laws of aerodynamic parameters with the rotation rate are presented and discussed. Full article
(This article belongs to the Special Issue Advances in Hypersonic Flows)
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20 pages, 8953 KiB  
Article
Evaluation of Thermodynamic and Chemical Kinetic Models for Hypersonic and High-Temperature Flow Simulation
by Wei Zhao, Xinglian Yang, Jingying Wang, Yongkang Zheng and Yue Zhou
Appl. Sci. 2023, 13(17), 9991; https://doi.org/10.3390/app13179991 - 4 Sep 2023
Cited by 2 | Viewed by 1922
Abstract
Significant thermochemical nonequilibrium effects always exist in the flow field around hypersonic vehicle at extreme flight condition. Previous studies have proposed various thermodynamic and chemical kinetic models to describe the thermochemical nonequilibrium processes in hypersonic and high-temperature flow. However, different selections from such [...] Read more.
Significant thermochemical nonequilibrium effects always exist in the flow field around hypersonic vehicle at extreme flight condition. Previous studies have proposed various thermodynamic and chemical kinetic models to describe the thermochemical nonequilibrium processes in hypersonic and high-temperature flow. However, different selections from such models might lead to remarkable variations in computational burden and prediction accuracy, which is still a matter of being unclear. In the present study, different commonly studied models for calculating the thermochemical nonequilibrium are systematically evaluated. The 5-, 7- and 11-species chemical kinetic models of Dunn-Kang, Gupta and Park together with the one- and two-temperature models are employed respectively to simulate the hypersonic flows over a standard cylinder with the radius of 1 m by HyFLOW, which is a commercial software based on the numerical solution of Navier-Stokes equations. Three flight conditions of FIRE Ⅱ classical flight trajectory are employed in the study. It shows that the differences between the results of the Dunn-Kang, Gupta and Park chemical kinetic models with the same number of species are small, but the Gupta model predicts the most conservative values of the wall heat flux. When only the order of magnitude and distribution trends of the pressure and wall heat flux are concerned, the one-temperature model combined with 5-species chemical reaction model can be used for a rapid prediction. While the accurate flow solution is required, the two-temperature model conjugated with Gupta 11-species model is recommended, especially at the conditions of extremely high altitude and Mach number. Full article
(This article belongs to the Special Issue Advances in Hypersonic Flows)
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