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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: 15 April 2025 | Viewed by 6370

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

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Further information on MDPI's Special Issue polices can be found here.

Published Papers (3 papers)

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Research

14 pages, 11754 KiB  
Article
Drag Reduction on the Basis of the Area Rule of the Small-Scale Supersonic Flight Experiment Vehicle Being Developed at Muroran Institute of Technology (Second Report)
by Kazuhide Mizobata, Taichi Mio and Katsuya Miyamoto
Aerospace 2024, 11(9), 777; https://doi.org/10.3390/aerospace11090777 - 20 Sep 2024
Viewed by 525
Abstract
A small-scale supersonic flight experiment vehicle named OWASHI is being developed at Muroran Institute of Technology as a flying testbed for verification of innovative technologies for high-speed atmospheric flights. Drag reduction in the transonic and supersonic regimes is quite crucial for attainability of [...] Read more.
A small-scale supersonic flight experiment vehicle named OWASHI is being developed at Muroran Institute of Technology as a flying testbed for verification of innovative technologies for high-speed atmospheric flights. Drag reduction in the transonic and supersonic regimes is quite crucial for attainability of its supersonic flights. This study aims to obtain configuration modification for transonic drag reduction on the basis of the so-called area rule. In order to prevent accumulation of compression waves, various profiles of the bottleneck and the bulge are designed by using arcs with constant and large radii and spline curves approximating them. Their effects are assessed through CFD analysis, wind tunnel tests, and wave drag analysis. As a result, an area-rule-based configuration with a sharpened conical nose and a large-radius bottleneck achieves significant drag reduction in a transonic Mach range, as well as 57-count (57 × 10−4) reduction at the design Mach number of 1.1. However, the drag reduction effects of bulges are small and apparent only in a narrow Mach range. On the other hand, in the practical vehicle configuration, rearward fuselage extension shows a large amount of drag reduction, whereas the addition of an intake cancels the drag reduction effects of area-rule-based configurations. Full article
(This article belongs to the Special Issue Research and Development of Supersonic Aircraft)
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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 - 9 Jan 2024
Cited by 1 | Viewed by 1431
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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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 3 | Viewed by 2699
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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Planned Papers

The below list represents only planned manuscripts. Some of these manuscripts have not been received by the Editorial Office yet. Papers submitted to MDPI journals are subject to peer-review.

Title: A Novel, Direct Matrix Solver for Supersonic BEM Systems
Authors: Cory Goates; Douglas Hunsaker
Affiliation: Utah State University
Abstract: For problems with very fine surface discretizations, the most time-consuming step of a boundary element method (BEM, also called a panel method) is solving the final linear system of equations. Many have already studied how to efficiently solve the dense, asymmetric systems which arise in elliptic BEMs. However, this has yet to be done for a BEM for supersonic aerodynamics, for which the governing PDE is hyperbolic and the linear system of equations is neither dense nor sparse. Hence, the efficient solution of the linear system of equations arising in a supersonic BEM is here considered. Due to the hyperbolic character of the governing PDE, the matrix equation which arises from a supersonic BEM has a large number of identically zero elements. A novel sorting algorithm is developed whereby these elements may be arranged into a useful structure with minimal cost. A novel direct solution method developed here based on fast Givens rotations and the QR decomposition then leverages this structure to solve the supersonic system of equations more quickly than traditional direct methods. This novel method is then compared to other direct and iterative matrix solvers and is shown to be more robust than iterative solvers and more efficient than other direct solvers, with a computational time complexity of approximately $O(N^{2.5})$.

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