Special Issue "Smart Wing Aircraft"

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

Deadline for manuscript submissions: 31 December 2021.

Special Issue Editor

Prof. Dr. Wolf-Reiner Krüger
E-Mail Website
Guest Editor
Institute of Aeroelasticity, German Aerospace Center (DLR), Loads Analysis and Design, Bunsenstr. 10, 37073 Göttingen, Germany
Interests: aircraft design; aeroelasticity; aircraft loads analysis; multibody dynamics

Special Issue Information

Dear Colleaugues,

Smart Wings are seen as a key factor to improve aircraft performance, increase passenger comfort beyond the state-of-the-art. As today’s transport aircraft have unquestionably reached a high level of quality, a combination of innovative techniques is required to obtain that ambitious goal. Various approaches for flow control promise a reduction of induced drag, e.g. by cruise-point dependent adaptation of the lift distribution, and of friction drag, e.g. by laminar flow. Passive load control methods like aeroelastic tailoring, and active load control techniques, in combination with new sensors like LIDAR systems or sensor networks, will help to reduce structural wing mass. New aircraft and wing design processes will capture the potential of the technologies for performance increase and load reduction, and will assess the impact on drag, aircraft mass and thus fuel burn reduction. Promising technologies will be tested in wind tunnel experiments, in UAV and full aircraft scale, making use of innovative sensing and data acquisition techniques.

The MDPI special issue will collect papers on the topic of Smart Wing Aircraft from those fields mentioned.

Prof. Dr. Wolf-Reiner Krüger
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 1600 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

  • design processes for smart wings
  • smart wing technologies for performance improvement
  • active and passive technologies for load alleviation
  • experimental testing and validation of smart wing technologies

Published Papers (2 papers)

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Research

Article
Unsteady Simulation of Transonic Buffet of a Supercritical Airfoil with Shock Control Bump
Aerospace 2021, 8(8), 203; https://doi.org/10.3390/aerospace8080203 - 26 Jul 2021
Viewed by 408
Abstract
The unsteady flow characteristics of a supercritical OAT15A airfoil with a shock control bump were numerically studied by a wall-modeled large eddy simulation. The numerical method was first validated by the buffet and nonbuffet cases of the baseline OAT15A airfoil. Both the pressure [...] Read more.
The unsteady flow characteristics of a supercritical OAT15A airfoil with a shock control bump were numerically studied by a wall-modeled large eddy simulation. The numerical method was first validated by the buffet and nonbuffet cases of the baseline OAT15A airfoil. Both the pressure coefficient and velocity fluctuation coincided well with the experimental data. Then, four different shock control bumps were numerically tested. A bump of height h/c = 0.008 and location xB/c = 0.55 demonstrated a good buffet control effect. The lift-to-drag ratio of the buffet case was increased by 5.9%, and the root mean square of the lift coefficient fluctuation was decreased by 67.6%. Detailed time-averaged flow quantities and instantaneous flow fields were analyzed to demonstrate the flow phenomenon of the shock control bumps. The results demonstrate that an appropriate “λ” shockwave pattern caused by the bump is important for the flow control effect. Full article
(This article belongs to the Special Issue Smart Wing Aircraft)
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Article
Design Process and Environmental Impact of Unconventional Tail Airliners
Aerospace 2021, 8(7), 175; https://doi.org/10.3390/aerospace8070175 - 28 Jun 2021
Viewed by 537
Abstract
The future of aviation depends on reducing the environmental impact of the aircraft. Unconventional configurations can be the change the industry needs to achieve that goal. Therefore, the development of a tool that allows analyzing these configurations will contribute to their being considered [...] Read more.
The future of aviation depends on reducing the environmental impact of the aircraft. Unconventional configurations can be the change the industry needs to achieve that goal. Therefore, the development of a tool that allows analyzing these configurations will contribute to their being considered more easily in future designs. This design procedure is based on an aerodynamic model and a weight methodology validated for unconventional tail designs. The load cases selected to size the structure were extracted from the certification regulations in force. In order to validate the methodology, the V-tail configuration was selected as a case study. The fuel savings reached with this tail configurations are around 0.7%, and the reduction in NOx emissions are even greater. Thus, the methodology has been validated and it can be easily adapted to other unconventional tail configurations. Full article
(This article belongs to the Special Issue Smart Wing Aircraft)
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