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Applied Sciences
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Applications of Aerodynamics in Aeronautical Engineering
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Applications of Aerodynamics in Aeronautical Engineering

A special issue of Applied Sciences (ISSN 2076-3417). This special issue belongs to the section "Aerospace Science and Engineering".

Deadline for manuscript submissions: closed (30 November 2024) | Viewed by 2328

Special Issue Editors

Dr. Jianhua Xu

E-Mail Website
Guest Editor
Department of Aerodynamics, School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China
Interests: near-space propeller; low Reynolds number aerodynamics; aerodynamic and multidisciplinary design optimization
Special Issues, Collections and Topics in MDPI journals
Prof. Dr. Yan Wang

E-Mail Website
Guest Editor
Department of Aerospace Engineering, College of Aerodynamics, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
Interests: computational mechanics methods and applications; drag reduction and optimal design of flight vehicles; numerical simulation of multi-phase flow; fluid–structure interaction; artificial intelligence and flow control
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

The progress in the theories and technologies of aerodynamics has significantly propelled the development of aircraft. The computational, design, and experimental methods of aerodynamics have become indispensable means for the innovation of advanced aircraft. In future aircraft design, aerodynamics will continue to play a significant role, but other aspects such as structure, control, stealth, and acoustics will also be important.

This Special Issue invites researchers and engineers from the field of aerodynamics to contribute original research, applied research, and reviews to demonstrate the application of aerodynamics in aeronautical engineering. Submissions on theoretical aspects or applications are both welcome, with the goal of showcasing the latest advancements in the field and providing practical insights for those involved in aeronautical engineering.

Dr. Jianhua Xu
Prof. Dr. Yan Wang
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. Applied Sciences 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 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

  • aeronautical engineering
  • advanced aircraft
  • aerodynamics

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Published Papers (2 papers)

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Research

33 pages, 15107 KiB  
Article
Experimental Study on Dynamic Force–Thermal Loading for Multi-Stage Telescopic Wings Based on the Dynamic Multi-Point Equivalent Method
by Hong Xiao, Shuailin Li, Hongwei Guo, Hualiang Liu, Guang Yang, Chunfeng Li and Jianguo Tao
Appl. Sci. 2025, 15(5), 2699; https://doi.org/10.3390/app15052699 - 3 Mar 2025
Viewed by 581
Abstract
To address the challenge of simulating force–thermal environmental loads on morphing wings during flight, this study proposes and validates a force–thermal simulation method based on servo loading. First, the aerodynamic loads on a multi-stage telescopic wing under extreme conditions were systematically analyzed to [...] Read more.
To address the challenge of simulating force–thermal environmental loads on morphing wings during flight, this study proposes and validates a force–thermal simulation method based on servo loading. First, the aerodynamic loads on a multi-stage telescopic wing under extreme conditions were systematically analyzed to identify the critical design loads. Subsequently, a force–thermal servo loading platform for multi-stage telescopic wings was designed and constructed to evaluate the performance of the wing’s morphing mechanism during flight. A dynamic multi-point equivalent method based on grid reconstruction was proposed and theoretically derived, along with simulations using a traditional multi-point load distribution method. Compared to the conventional equal-area division method, the simulation results demonstrated a significant improvement in deformation fitting accuracy using the proposed method. Finally, force–thermal servo loading experiments were conducted on a prototype of the multi-stage telescopic wing. The results verified that the proposed loading method can accurately simulate load variations during flight, with experimental trends closely aligning with simulation predictions. Additionally, the experiments demonstrated the loading system’s rapid response capability, confirming the feasibility and potential of the designed loading platform and theoretical model. This research provides critical technical support and theoretical foundations for the design, validation, and force–thermal environment simulation of future multidimensional morphing wings. Full article
(This article belongs to the Special Issue Applications of Aerodynamics in Aeronautical Engineering)
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27 pages, 19850 KiB  
Article
Aerodynamic Optimization and Characterization of a Ducted Tail for a Box-Launched Aircraft
by Huayu Jia, Huilong Zheng, Hong Zhou and Qian Zhang
Appl. Sci. 2024, 14(15), 6496; https://doi.org/10.3390/app14156496 - 25 Jul 2024
Cited by 2 | Viewed by 1101
Abstract
The tail wing of box-launched aircraft needs to be folded in the launch box, which can easily cause malfunctions during flight deployment. This article presents a ducted tail wing aircraft that does not require folding of the tail wing. To address the nonlinear [...] Read more.
The tail wing of box-launched aircraft needs to be folded in the launch box, which can easily cause malfunctions during flight deployment. This article presents a ducted tail wing aircraft that does not require folding of the tail wing. To address the nonlinear problem of lift coefficient in the ducted tail, an aerodynamic optimization method for ducted tails based on the sparrow search algorithm with back-propagation (SSA-BP) neural network approximate model and multi-objective genetic algorithm fusion is proposed, with the goal of improving the lift-to-drag ratio and linearization degree of the lift curve. The linearization degree of the optimized tail lift coefficient curve is significantly improved, and the lift-to-drag ratio is significantly improved under cruising conditions. Based on this optimization result, the shape of the tail wing and fuselage combination was optimized, and the optimal configuration of the ducted tail wing aircraft was selected, providing a reference for the design of ducted tail wing aircraft. Full article
(This article belongs to the Special Issue Applications of Aerodynamics in Aeronautical Engineering)
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