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Applied Sciences
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Application of Fluid Mechanics and Aerodynamics in Aerospace
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Application of Fluid Mechanics and Aerodynamics in Aerospace

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

Deadline for manuscript submissions: 31 December 2025 | Viewed by 3024

Special Issue Editors

Prof. Dr. Yue Zhang

E-Mail Website
Guest Editor
College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
Interests: internal flow aerodynamics; shock wave/boundary layer interaction; aircraft engine inlet design
Prof. Dr. Zhenlong Wu

E-Mail Website
Guest Editor
College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
Interests: fluid dynamics; aviation and the environment
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

Fluid mechanics and aerodynamics are fundamental disciplines that are indispensable to the aerospace and aviation sectors, providing the requisite theoretical foundations and technological infrastructure for the precipitous growth of the aerospace industry. In a concerted effort to galvanize academic discourse and to foster technological breakthroughs within this domain, we are delighted to announce a call for papers for a Special Issue entitled “Application of Fluid Mechanics and Aerodynamics in Aerospace”. The primary aim of this Special Issue is to collate cutting-edge research findings in the fields of fluid mechanics and aerodynamics, and to examine the critical roles that these scientific disciplines occupy within aerospace technology.

We are therefore interested in articles that investigate applications of fluid mechanics and aerodynamics in aerospace. Potential topics include, but are not limited to, the following:

  1. The application of fluid mechanics in aerospace propulsion systems;
  2. Aerodynamic optimization and innovation in aircraft design;
  3. The utilization of fluid mechanics and aerodynamics in spacecraft thermal protection technology;
  4. Investigating fluid mechanics and aerodynamics challenges pertaining to unmanned aerial vehicles (UAVs);
  5. Pivotal technologies in fluid mechanics and aerodynamics of hypersonic vehicles;
  6. The role of fluid mechanics and aerodynamics in spacecraft attitude control systems;
  7. Emerging methodologies and technologies for testing in fluid mechanics and aerodynamics;
  8. Additional aerospace applications allied with fluid mechanics and aerodynamics research.

Prof. Dr. Yue Zhang
Prof. Dr. Zhenlong Wu
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

  • supersonic flow
  • hypersonic flow
  • flow control
  • propulsion
  • shock wave
  • aerodynamics
  • scramjet
  • ramjet

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

Published Papers (4 papers)

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Research

14 pages, 1864 KiB  
Article
Lifting-Line Predictions for the Ideal Twist Effectiveness of Spanwise Continuous and Discrete Control Surfaces
by Zachary S. Montgomery, Douglas F. Hunsaker and James J. Joo
Appl. Sci. 2025, 15(6), 3383; https://doi.org/10.3390/app15063383 - 19 Mar 2025
Viewed by 268
Abstract
Modern materials and manufacturing technologies have allowed the construction of morphing wings that are able to continuously vary certain airfoil parameters such as twist, camber, or control surface deflection as a function of span. This work presents a twist effectiveness parameter as a [...] Read more.
Modern materials and manufacturing technologies have allowed the construction of morphing wings that are able to continuously vary certain airfoil parameters such as twist, camber, or control surface deflection as a function of span. This work presents a twist effectiveness parameter as a means of comparing the ideal aerodynamic efficiency of spanwise continuous control surfaces (morphing wings) and spanwise discrete control surfaces (standard wings). A numerical algorithm is used to compute the twist effectiveness of both continuous and discrete control-surface designs over a wide range of planform shapes with evenly spaced actuation for inviscid, incompressible flow. Results included here show that using continuous control surfaces instead of discrete control surfaces reduces induced drag by less than 5% for most applications. Full article
(This article belongs to the Special Issue Application of Fluid Mechanics and Aerodynamics in Aerospace)
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27 pages, 49547 KiB  
Article
Study of Airfoil Deflections for Unsteady Aerodynamics Optimization in Pitching Airfoils
by William Refling, Charles Fabijanic, Thomas Sprengeler, Yildirim Bora Suzen and Jordi Estevadeordal
Appl. Sci. 2025, 15(5), 2455; https://doi.org/10.3390/app15052455 - 25 Feb 2025
Viewed by 453
Abstract
Camber deflection concepts for a VR-12 rotorcraft airfoil were studied for the optimization of unsteady aerodynamics, including dynamic stall conditions and wing–wing interactions during pitching. The designs are based on deflections of the leading edge and trailing edge sections of the airfoil. The [...] Read more.
Camber deflection concepts for a VR-12 rotorcraft airfoil were studied for the optimization of unsteady aerodynamics, including dynamic stall conditions and wing–wing interactions during pitching. The designs are based on deflections of the leading edge and trailing edge sections of the airfoil. The deflection parameters were initially established using Computational Fluid Dynamics (CFD). Results from CFD and Particle Image Velocimetry (PIV) were generated for various leading and trailing edge deflection combinations for comparison of their performances. The conditions of this study are for a Reynolds number of 250,000 and pitching reduced frequency of 0.04, representing a medium regime of rotorcraft operations. Linear tandem tests were performed to simulate unsteady wing–wing interactions. The effects of the deflections are discussed and compared to the baseline. Significant benefits are observed, notably dynamic stall mitigation from the leading edge (LE) deflected wing for certain angles of attack and decrease in the separation regions. Overall, from the numerical simulations and the experimental data fields, the LE deflection provides about 10% improvement, followed by the combined LE&TE deflections (8%). It is also found that combining various deflections can provide a performance increase over drastically different areas of the range of angle of attack. Full article
(This article belongs to the Special Issue Application of Fluid Mechanics and Aerodynamics in Aerospace)
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33 pages, 6254 KiB  
Article
Development of a Reduced Order Model-Based Workflow for Integrating Computer-Aided Design Editors with Aerodynamics in a Virtual Reality Dashboard: Open Parametric Aircraft Model-1 Testcase
by Andrea Lopez and Marco E. Biancolini
Appl. Sci. 2025, 15(2), 846; https://doi.org/10.3390/app15020846 - 16 Jan 2025
Viewed by 785
Abstract
In this paper, a workflow for creating advanced aerodynamics design dashboards is proposed. A CAD modeler is directly linked to the CFD simulation results so that the designer can explore in real time, assisted by virtual reality (VR), how shape parameters affect the [...] Read more.
In this paper, a workflow for creating advanced aerodynamics design dashboards is proposed. A CAD modeler is directly linked to the CFD simulation results so that the designer can explore in real time, assisted by virtual reality (VR), how shape parameters affect the aerodynamics and choose the optimal combination to optimize performance. In this way, the time required for the conception of a new component can be drastically reduced because, even at the preliminary stage, the designer has all the necessary information to make more thoughtful choices. Thus, this work sets a highly ambitious and innovative goal: to create a smart design dashboard where every shape parameter is directly and in real-time linked to the results of the high-fidelity analyses. The OPAM (Open Parametric Aircraft Model), a simplified model of the Boeing 787, was considered as a case study. CAD parameterization and mesh morphing were combined to generate the design points (DPs), while Reduced Order Models (ROMs) were developed to link the results of the CFD analyses to the chosen parameterization. The ROMs were exported as FMUs (Functional Mockup Units) to be easily managed in any environment. Finally, a VR design dashboard was created in the Unity environment, enabling the interaction with the geometric model in order to observe in a fully immersive and intuitive environment how each shape parameter affects the physics involved. The MetaQuest 3 headset has been selected for these tests. Thus, the use of VR for a design platform represents another innovative aspect of this work. Full article
(This article belongs to the Special Issue Application of Fluid Mechanics and Aerodynamics in Aerospace)
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22 pages, 29982 KiB  
Article
Numerical Study on the Effects of Boundary Layer Suction on Flow in the Sectorial Transonic Cascade Under Imitated Near-Stall Condition
by Ruixing Liang, Huawei Lu, Zhitao Tian, Hong Wang and Shuang Guo
Appl. Sci. 2025, 15(1), 76; https://doi.org/10.3390/app15010076 - 26 Dec 2024
Cited by 1 | Viewed by 712
Abstract
In the experimental study of a compressor’s cascade under the near-stall condition, the test bench has the disadvantages of high risk and high maintenance cost. This paper explores a method of using the inlet guide vane to imitate near-stall conditions instead of the [...] Read more.
In the experimental study of a compressor’s cascade under the near-stall condition, the test bench has the disadvantages of high risk and high maintenance cost. This paper explores a method of using the inlet guide vane to imitate near-stall conditions instead of the rotor. The suction groove is set in the sectorial cascade so as to explore the aerodynamic performance of the fluid and the change in the flow field structure. Three different schemes are proposed along the suction surface, and the results indicate that the EW2 scheme, which is located behind the separation starting point and near the vortex core of the separation vortex, has the best performance. The suction groove weakens the downwash caused by the boundary layer on the upper endwall, reducing the radial dimension of the corner and suppressing separation. Suction on the upper endwall also increases the pressure difference in the radial direction of the flow passage, resulting in a slight increase in the suction-side horseshoe vortex (HSV) at the hub. An overall loss reduction of 9.4% is achieved when the suction coefficient is 46%, and the corner separation is most effectively suppressed while ensuring that the HSV at the hub only slightly increases. Full article
(This article belongs to the Special Issue Application of Fluid Mechanics and Aerodynamics in Aerospace)
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