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Aerospace
Special Issues
Research and Development of Supersonic Aircraft
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Research and Development of Supersonic Aircraft

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

Deadline for manuscript submissions: 30 June 2024 | Viewed by 5091

Special Issue Editors

Prof. Dr. Masahiro Kanazaki

E-Mail Website
Guest Editor
Department of Aeronautics and Astronautics, Tokyo Metropolitan University, Hachioji, Tokyo 192-0397, Japan
Interests: aircraft design; spacecraft design; design optimization; computational fluid dynamics; supersonic aircraft
Dr. Takahiro Ukai

E-Mail Website
Guest Editor
Osaka Institute of Technology, Omiya, Asahi Ward, Osaka 535-8585, Japan
Interests: experimental fluid dynamics; supersonic flow; flow diagnostic techniques

Special Issue Information

Dear Colleagues,

Boom Supersonic's Overture supersonic transport (SST) has been developed with the investment of Japan Airlines (JAL), which has acquired preferential ordering rights for 20 aircraft. Airlines, including United Airlines, American Airlines, and JAL, plan to purchase over 100 Overture aircraft. Overture is expected to connect Tokyo and Seattle with a transit time of fewer than six hours, which is approximately half the time required by current passenger aircraft.

The realization of Overture is highly significant because it is the first commercial SST since Concorde. Various studies are being performed globally to develop the next generation of Overture. Improving fuel economy through highly efficient airframe designs and engine integration is currently the most significant issue in SST research. Sonic boom mitigation is also a unique challenge.

This Special Issue, “The R&D of Supersonic Aircraft,” invites submissions concerning the research and development of next-generation SST from the viewpoint of aerodynamics, including sonic boom mitigation, structural and flight dynamics, and other novel concepts.

Prof. Dr. Masahiro Kanazaki
Dr. Takahiro Ukai
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

  • supersonic aircraft design

  • experiments

  • computer simulations

  • aircraft design

  • flight experiments

  • sonic boom mitigation

  • low emission technologies

Published Papers (3 papers)

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Research

21 pages, 20314 KiB  
Article
Robust Design Optimization of Supersonic Biplane Airfoil Using Efficient Uncertainty Analysis Method for Discontinuous Problem
by Kyohei Hanazaki and Wataru Yamazaki
Aerospace 2024, 11(1), 64; https://doi.org/10.3390/aerospace11010064 - 09 Jan 2024
Viewed by 906
Abstract
Busemann’s supersonic biplane airfoil can reduce wave drag through shock interactions at its designed freestream Mach number. However, a choking phenomenon occurs with a decrease in the freestream Mach number, and the drag coefficient increases significantly, resulting in an aerodynamic problem with a [...] Read more.
Busemann’s supersonic biplane airfoil can reduce wave drag through shock interactions at its designed freestream Mach number. However, a choking phenomenon occurs with a decrease in the freestream Mach number, and the drag coefficient increases significantly, resulting in an aerodynamic problem with a discontinuous change in the performance function. In this study, an uncertainty analysis method, the divided inexpensive Monte Carlo simulation (IMCS), is proposed to solve discontinuous problems efficiently and is applied to Busemann’s biplane airfoil. In the divided IMCS, the discontinuity point is determined using a simple sampling method. The uncertainty input space is divided at the detected discontinuity point, and a surrogate model is constructed for each space. Uncertainty analysis was performed using the constructed surrogate models, and the results of the divided IMCS showed qualitative agreement with those of the conventional Monte Carlo simulation, which is the most straightforward uncertainty analysis method. Moreover, the divided IMCS significantly reduced the computational cost of the uncertainty analysis. A robust design optimization of the supersonic biplane airfoil was performed using the divided IMCS, yielding more robust designs than Busemann’s biplane airfoil. The usefulness of the divided IMCS for uncertainty analysis of discontinuous problems was confirmed. Full article
(This article belongs to the Special Issue Research and Development of Supersonic Aircraft)
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14 pages, 5215 KiB  
Article
Characteristics of Vortices around Forward Swept Wing at Low Speeds/High Angles of Attack
by Masahiro Kanazaki and Nao Setoguchi
Aerospace 2023, 10(9), 790; https://doi.org/10.3390/aerospace10090790 - 08 Sep 2023
Viewed by 1457
Abstract
The forward-swept wing (FSW), one of the wing planforms used in aircraft, is known for its high performance in reducing wave drag. Additionally, a study has shown that this wing planform can mitigate sonic booms, which pose a significant challenge to achieving supersonic [...] Read more.
The forward-swept wing (FSW), one of the wing planforms used in aircraft, is known for its high performance in reducing wave drag. Additionally, a study has shown that this wing planform can mitigate sonic booms, which pose a significant challenge to achieving supersonic transport (SST). Therefore, FSW is expected to find applications in future SST aircraft owing to aerodynamic advantages at high speeds. However, there is a lack of sufficient knowledge and systematization to improve aerodynamic performance at low speeds and high angles of attack during takeoff and landing. These are crucial for practical implementation. Although the aerodynamic benefits of an FSW in high-speed flight can be harnessed using advanced structural and control technologies, the realization of SST using an FSW is challenging without enhanced research on low-speed aerodynamics. This study explores the practical aerodynamic knowledge of FSWs. We utilized a numerical simulation based on the Navier–Stokes equation and focused on investigating wake vortex phenomena. Our simulation included various wing planforms, including backward-swept wings (BSWs). The results revealed the presence of vortices with lateral axes emanating from the FSW, while longitudinal vortices were observed in the BSW. Based on these results, we developed a theoretical hypothesis for the vortex structure around an FSW. Full article
(This article belongs to the Special Issue Research and Development of Supersonic Aircraft)
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21 pages, 6215 KiB  
Article
Low-Boom Design for Supersonic Transport with Canard and Forward-Swept Wings Using Equivalent Area Design Method
by Yuki Kishi, Risato Yashiro and Masahiro Kanazaki
Aerospace 2023, 10(8), 717; https://doi.org/10.3390/aerospace10080717 - 16 Aug 2023
Cited by 1 | Viewed by 1700
Abstract
Forward-swept wings can be expected to be lower-boom planforms with similar amount of drag as backward-swept wings because of their good lift distributions. In this study, the equivalent area distribution of a ten-seater supersonic forward-swept wing aircraft with a canard was designed to [...] Read more.
Forward-swept wings can be expected to be lower-boom planforms with similar amount of drag as backward-swept wings because of their good lift distributions. In this study, the equivalent area distribution of a ten-seater supersonic forward-swept wing aircraft with a canard was designed to obtain design knowledge for leading boom reduction. The equivalent area distribution of the aircraft was calculated by solving the compressible Euler equation. A feasible target equivalent area distribution was generated based on Darden’s method and compared with the equivalent area distribution. To achieve a closer match in terms of lift and geometry with the target, the main wing planform and the position of the main wing along the body and vertical axes were modified. The low-boom performances were evaluated using the extended Burgers equation. The design results indicated that the forward-swept wing configuration with a canard could divide the single peak of the leading boom into two peaks. Thus, the sonic boom strength of the canard configuration was 2.5 PLdB lower than that of the configuration without the canard wing. Full article
(This article belongs to the Special Issue Research and Development of Supersonic Aircraft)
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