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Energies
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Aerodynamics and Aerothermodynamics of High-Speed Vehicles
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Aerodynamics and Aerothermodynamics of High-Speed Vehicles

A special issue of Energies (ISSN 1996-1073). This special issue belongs to the section "E: Electric Vehicles".

Deadline for manuscript submissions: closed (31 December 2021) | Viewed by 12654

Special Issue Editors

Dr. Giuseppe Pezzella

E-Mail Website
Guest Editor
Engineering Department, Università della Campania “L. Vanvitelli”, Via Roma 29, I-81031 Aversa, Italy
Interests: aerodynamics; aerothermodynamics; aircraft; re-entry vehicles
Special Issues, Collections and Topics in MDPI journals
Prof. Dr. Antonio Viviani

E-Mail Website
Guest Editor
Engineering Department, University of Campania “Luigi Vanvitelli” (UCLV), Via Roma 29, 81031 Aversa, CE, Italy
Interests: aerodynamics; aerothermodynamics; aircraft; microgravity

Special Issue Information

Dear Colleagues,

Nowadays, market globalization and scientific/commercial exploitation of space strongly demand reliable, efficient, and affordable high-speed transportation systems. Although great progress and success have been accomplished in this field, flying at high supersonic/hypersonic speeds is still challenging in aerospace engineering. In fact, in order to achieve this goal, several design issues must be addressed, such as vehicle aerodynamics and aerothermodynamics, aeroshape design optimization, aerodynamic heating, and boundary layer transition. Further, the idea of operating an aircraft at high speeds, e.g., supersonic and hypersonic Mach, is viewed differently among members of the scientific community.

In this framework, the aim of this Special Issue is to allow researchers and engineers to collect valuable works that focus on high-speed aircraft, especially on vehicle aerodynamic and aerothermodynamic designs. For instance, the extreme loading environment of high-speed flows necessitates the design of advanced aeroshapes that are able to sustain large heat transfer and mechanical loading conditions while providing aerodynamic forces to sustain flight. Therefore, this Special Issue intends to explore all the disciplines and design goals, which represent research topics, and/or overviews of the program development of several research centers and industries all over the world. Welcomed research works include those related to high-speed (e.g., supersonic and hypersonic) aircraft aerodynamic and aerothermodynamic designs, especially those related to:

  • aeroshape design;
  • computational fluid dynamics;
  • hypersonics;
  • conjugate heat transfer problem;
  • thermo-chemical non-equilibrium;
  • radiative heat transfer;
  • catalyticity;
  • aeroshape optimization;
  • capsule;
  • sample return missions;
  • fluid–structure interaction;
  • heat transfer;
  • shock-wave boundary-layer interaction (SWBLI);
  • shock–shock interaction (SSI);
  • boundary layer transition;
  • flow transition prediction;
  • wind tunnel test;
  • numerical rebuilding of experimental test campaign;
  • vehicle aerodynamics;
  • vehicle aerothermodynamics;
  • aerodynamic database modeling;
  • aerothermodynamic database modeling;
  • multidisciplinary design optimization (MDO);
  • high-speed flows;
  • scramjet propulsion;
  • in-flight experimentation;
  • extrapolation to flight;
  • viscous interaction;
  • lifting body;
  • winged body;
  • waverider

Therefore, this Special Issue delves into the aeroshape design of advanced configurations that will allow high-speed vehicles to be faster, quieter, and more economical than before.

Furthermore, the vision of high-speed flow issues and the challenges to achieving the dream of affordable high-speed travel will also be discussed.

Achieving the above-mentioned goals will make the possibility of high-speed air travel a reality.

Prof. Dr. Giuseppe Pezzella
Prof. Dr. Antonio Viviani
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. Energies 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 2600 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

  • high-speed flow
  • supersonic flow
  • hypersonic flow
  • aerodynamics, aerothermodynamics
  • scramjet propulsion
  • computational fluid dynamics

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Published Papers (3 papers)

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Research

27 pages, 2768 KiB  
Article
Multi-Objective RANS Aerodynamic Optimization of a Hypersonic Intake Ramp at Mach 5
by Francesco De Vanna, Danilo Bof and Ernesto Benini
Energies 2022, 15(8), 2811; https://doi.org/10.3390/en15082811 - 12 Apr 2022
Cited by 15 | Viewed by 3384
Abstract
The work describes a systematic optimization strategy for designing hypersonic inlet intakes. A Reynolds-averaged Navier-Stokes database is mined using genetic algorithms to develop ideal designs for a priori defined targets. An intake geometry from the literature is adopted as a baseline. Thus, a [...] Read more.
The work describes a systematic optimization strategy for designing hypersonic inlet intakes. A Reynolds-averaged Navier-Stokes database is mined using genetic algorithms to develop ideal designs for a priori defined targets. An intake geometry from the literature is adopted as a baseline. Thus, a steady-state numerical assessment is validated and the computational grid is tuned under nominal operating conditions. Following validation tasks, the model is used for multi-objective optimization. The latter aims at minimizing the drag coefficient while boosting the static and total pressure ratios, respectively. The Pareto optimal solutions are analyzed, emphasizing the flow patterns that result in the improvements. Although the approach is applied to a specific setup, the method is entirely general, offering a valuable flowchart for designing super/hypersonic inlets. Notably, because high-quality computational fluid dynamics strategies drive the innovation process, the latter accounts for the complex dynamics of such devices from the early design stages, including shock-wave/boundary-layer interactions and recirculating flow portions in the geometrical shaping. Full article
(This article belongs to the Special Issue Aerodynamics and Aerothermodynamics of High-Speed Vehicles)
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20 pages, 4377 KiB  
Article
Aerodynamic Analysis of a Supersonic Transport Aircraft at Landing Speed Conditions
by Andrea Aprovitola, Pasquale Emanuele Di Nuzzo, Giuseppe Pezzella and Antonio Viviani
Energies 2021, 14(20), 6615; https://doi.org/10.3390/en14206615 - 13 Oct 2021
Cited by 4 | Viewed by 4292
Abstract
Supersonic flight for commercial aviation is gaining a renewed interest, especially for business aviation, which demands the reduction of flight times for transcontinental routes. So far, the promise of civil supersonic flight has only been afforded by the Concorde and Tupolev T-144 aircraft. [...] Read more.
Supersonic flight for commercial aviation is gaining a renewed interest, especially for business aviation, which demands the reduction of flight times for transcontinental routes. So far, the promise of civil supersonic flight has only been afforded by the Concorde and Tupolev T-144 aircraft. However, little or nothing can be found about the aerodynamics of these aeroshapes, the knowledge of which is extremely interesting to obtain before the development of the next-generation high-speed aircraft. Therefore, the present research effort aimed at filling in the lack of data on a Concorde-like aeroshape by focusing on evaluating the aerodynamics of a complete aircraft configuration under low-speed conditions, close to those of the approach and landing phase. In this framework, the present paper focuses on the CFD study of the longitudinal aerodynamics of a Concorde-like, tailless, delta-ogee wing seamlessly integrated onto a Sears–Haack body fuselage, suitable for civil transportation. The drag polar at a Mach number equal to 0.24 at a 30 m altitude was computed for a wide range of angles of attack (0∘,60∘), with a steady RANS simulation to provide the feedback of the aerodynamic behaviour post breakdown, useful for a preliminary design. The vortex-lift contribution to the aerodynamic coefficients was accounted for in the longitudinal flight condition. The results were in agreement with the analytical theory of the delta-wing. Flowfield sensitivity to the angle of attack at near-stall and post-stall flight attitudes confirmed the literature results. Furthermore, the longitudinal static stability was addressed. The CFD simulation also evidenced a static instability condition arising for 15∘≤α≤20∘ due to vortex breakdown, which was accounted for. Full article
(This article belongs to the Special Issue Aerodynamics and Aerothermodynamics of High-Speed Vehicles)
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Graphical abstract

28 pages, 14055 KiB  
Article
Aerodynamic Characterization of Hypersonic Transportation Systems and Its Impact on Mission Analysis
by Nicole Viola, Pietro Roncioni, Oscar Gori and Roberta Fusaro
Energies 2021, 14(12), 3580; https://doi.org/10.3390/en14123580 - 16 Jun 2021
Cited by 27 | Viewed by 3386
Abstract
This paper aims to provide technical insights on the aerodynamic characterization activities performed in the field of the H2020 STRATOFLY project, for the Mach 8 waverider reference configuration. Considering the complexity of the configuration to be analyzed at conceptual/preliminary design stage, a build-up [...] Read more.
This paper aims to provide technical insights on the aerodynamic characterization activities performed in the field of the H2020 STRATOFLY project, for the Mach 8 waverider reference configuration. Considering the complexity of the configuration to be analyzed at conceptual/preliminary design stage, a build-up approach has been adopted. The complexity of the aerodynamic model increases incrementally, from the clean external configuration up to the complete configuration, including propulsion systems elements and flight control surfaces. At each step, the aerodynamic analysis is complemented with detailed mission analysis, in which the different versions of the aerodynamic databases are used as input for the trajectory simulation. eventually, once the contribution to the aerodynamic characterization of flight control surfaces is evaluated, stability and trim analysis is carried out. The comparison of the results obtained through the different mission analysis campaigns clearly shows that the accuracy of aerodynamic characterization may determine the feasibility or unfeasibility of a mission concept. Full article
(This article belongs to the Special Issue Aerodynamics and Aerothermodynamics of High-Speed Vehicles)
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