Special Issue "Aerodynamic Design of Next Generation High-Speed Aircrafts"

A special issue of Aerospace (ISSN 2226-4310).

Deadline for manuscript submissions: closed (31 March 2019).

Special Issue Editors

Prof. Dr. Giuseppe Pezzella
Website1 Website2
Guest Editor
Engineering Department, University of Campania “Luigi Vanvitelli” (UCLV), Via Roma 29, 81031, Aversa, CE, Italy
Interests: aerodynamics; aerothermodynamics; aeronautics; astronautics
Special Issues and Collections in MDPI journals
Prof. Dr. Antonio Viviani
Website
Co-Guest Editor
Engineering Department, University of Campania “Luigi Vanvitelli” (UCLV), Via Roma 29, 81031, Aversa, CE, Italy
Interests: aerodynamics; aeronautics; fluid dynamics; microgravity
Special Issues and Collections in MDPI journals

Special Issue Information

Dear Colleagues,

High-speed travels represent the next frontier of passenger transportation, to and from space, as well as for civil flights. Flying in excess of Mach 5 is a dream that has been around for over 40 years. Today, market globalization and scientific explorations of space highlight that to fly higher and faster is even more 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, boundary layer transition, etc. Further, the scientific community looks at the idea of operating an aircraft at high-speeds, i.e., supersonic and hypersonic Mach, differently.

In this framework, the aim of this Special Issue is to allow researchers and engineers to collect valuable works focusing on high-speed aircrafts, especially on vehicle aerodynamic and aerothermodynamic designs. For instance, the extreme loading environment of high-speed flows demand the design of advanced aeroshapes, 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 program development, of several research centers and industries all over the world. In particular, it welcomes research works related to high-speed (e.g., supersonic and hypersonic) aircraft aerodynamic and aerothermodynamic design, and especially on:

  • 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 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 achieve the dream of affordable high-speed travel will be also discussed.

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

Dr. Giuseppe Pezzella
Prof. Dr. Antonio Viviani
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 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 1000 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.

Published Papers (1 paper)

Order results
Result details
Select all
Export citation of selected articles as:

Research

Open AccessArticle
Correlation Analysis of Separation Shock Oscillation and Wall Pressure Fluctuation in Unstarted Hypersonic Inlet Flow
Aerospace 2019, 6(1), 8; https://doi.org/10.3390/aerospace6010008 - 10 Jan 2019
Abstract
The flow field in a hypersonic inlet model at a design point of M = 6 has been studied experimentally. The focus of the current study is to present the time-resolved flow characteristics of separation shock around the cowl and the correlation between [...] Read more.
The flow field in a hypersonic inlet model at a design point of M = 6 has been studied experimentally. The focus of the current study is to present the time-resolved flow characteristics of separation shock around the cowl and the correlation between the separation shock oscillation induced by the unstart flow and the wall pressure fluctuation when the inlet is in a state of unstart. High-speed Schlieren flow visualization is used to capture the transient shock structure. High-frequency pressure transducers are installed on the wall around both the cowl and isolator areas to detect the dynamic pressure distribution. A schlieren image quantization method based on gray level detection and calculation is developed to analyze the time-resolved spatial structure of separation shock. Results indicate that the induced separation shock oscillation and the wall pressure fluctuation are closely connected, and they show the same frequency variation characteristics. The unsteady flow pattern of the “little buzz” and “big buzz” modes are clarified based on time-resolved Schlieren images of separation shock. Furthermore, the appropriate location of the pressure transducers is determined on the basis of the combined analysis of fluctuating wall-pressure and oscillating separation shock data. Full article
(This article belongs to the Special Issue Aerodynamic Design of Next Generation High-Speed Aircrafts)
Show Figures

Graphical abstract

Back to TopTop