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Applied Sciences
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Computational Fluid Dynamics for Aerospace and Aeronautical Applications
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Computational Fluid Dynamics for Aerospace and Aeronautical Applications

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

Deadline for manuscript submissions: 20 October 2026 | Viewed by 2948

Special Issue Editors

Prof. Dr. Elisabeth Lacazedieu

E-Mail Website
Guest Editor
Laboratoire de Mécanique des Structures Industrielles Durables, Clamart, France
Interests: numerical modeling; computational fluid dynamics; fluid dynamics mechanics; numerical simulation; fluid mechanics; CFD simulation; computational fluid mechanics; numerical analysis
Dr. Wei Kang

E-Mail Website
Guest Editor
School of Astronautics, Northwestern Polytechnical University, Xi'an, China
Interests: aeroelasticity; fluid-structure interaction; flow control; CFD

Special Issue Information

Dear Colleagues,

Computational Fluid Dynamics (CFD) is a pivotal tool in aerospace and aeronautical applications, offering insights into fluid flow behaviors and enabling the optimization of designs across various disciplines. This Special Issue highlights the innovative use of CFD in addressing complex problems, e.g., new findings in aeronautic and aerospace engineering.

This Special Issue aims to explore the diverse aerospace and aeronautical Applications of CFD, emphasizing its role in enhancing performance, optimizing designs, and fostering innovation in engineering fields.

In this Special Issue, original research articles and reviews are welcome. Research areas may include (but are not limited to) the following:

  • CFD methodology;
  • Flow pattern analysis
  • Fluid–Structure Interactions;
  • CFD-based optimization;
  • AI in CFD;
  • CFD applications in aeronautical engineering;
  • CFD applications in aerospace engineering.

Prof. Dr. Elisabeth Lacazedieu
Dr. Wei Kang
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 250 words) can be sent to the Editorial Office for assessment.

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

  • computational fluid dynamics
  • numerical simulations
  • optimization
  • fluid–structure interactions
  • aeroelasticity
  • flow control
  • AI-based computational fluid dynamics

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Published Papers (3 papers)

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Research

34 pages, 10588 KB  
Article
Effects of Momentum-FluxRatio on POD and SPOD Modes in High-Speed Crossflow Jets
by Subhajit Roy and Guillermo Araya
Appl. Sci. 2026, 16(3), 1424; https://doi.org/10.3390/app16031424 - 30 Jan 2026
Viewed by 238
Abstract
High-speed jet-in-crossflow (JICF) configurations are central to several aerospace applications, including turbine-blade film cooling, thrust vectoring, and fuel or hydrogen injection in combusting or reacting flows. This study employs high-fidelity direct numerical simulations (DNS) to investigate the dynamics of a supersonic jet (Mach [...] Read more.
High-speed jet-in-crossflow (JICF) configurations are central to several aerospace applications, including turbine-blade film cooling, thrust vectoring, and fuel or hydrogen injection in combusting or reacting flows. This study employs high-fidelity direct numerical simulations (DNS) to investigate the dynamics of a supersonic jet (Mach 3.73) interacting with a subsonic crossflow (Mach 0.8) at low Reynolds numbers. Three momentum-flux ratios (J = 2.8, 5.6, and 10.2) are considered, capturing a broad range of jet–crossflow interaction regimes. Turbulent inflow conditions are generated using the Dynamic Multiscale Approach (DMA), ensuring physically consistent boundary-layer turbulence and accurate representation of jet–crossflow interactions. Modal decomposition via proper orthogonal decomposition (POD) and spectral POD (SPOD) is used to identify the dominant spatial and spectral features of the flow. Across the three configurations, near-wall mean shear enhances small-scale turbulence, while increasing J intensifies jet penetration and vortex dynamics, producing broadband spectral gains. Downstream of the jet injection, the spectra broadly preserve the expected standard pressure and velocity scaling across the frequency range, except at high frequencies. POD reveals coherent vortical structures associated with shear-layer roll-up, jet flapping, and counter-rotating vortex pair (CVP) formation, with increasing spatial organization at higher momentum ratios. Further, POD reveals a shift in dominant structures: shear-layer roll-up governs the leading mode at high J, whereas CVP and jet–wall interactions dominate at lower J. Spectral POD identifies global plume oscillations whose Strouhal number rises with J, reflecting a transition from slow, wall-controlled flapping to faster, jet-dominated dynamics. Overall, the results demonstrate that the momentum-flux ratio (J) regulates not only jet penetration and mixing but also the hierarchy and characteristic frequencies of coherent vortical, thermal, and pressure and acoustic structures. The predominance of shear-layer roll-up over counter-rotating vortex pair (CVP) dynamics at high J, the systematic upward shift of plume-oscillation frequencies, and the strong analogy with low-frequency shock–boundary-layer interaction (SBLI) dynamics collectively provide new mechanistic insight into the unsteady behavior of supersonic jet-in-crossflow flows. Full article
(This article belongs to the Special Issue Computational Fluid Dynamics for Aerospace and Aeronautical Applications)
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26 pages, 4825 KB  
Article
Analysis of the Impact of Typical Sand and Dust Weather in Southern Xinjiang on the Aerodynamic Performance of Aircraft Airfoils
by Mingzhao Li, Afang Jin, Yushang Hu and Huijie Li
Appl. Sci. 2025, 15(20), 10917; https://doi.org/10.3390/app152010917 - 11 Oct 2025
Viewed by 762
Abstract
As aviation operations extend into complex natural environments, dust particles present significant challenges to flight stability and safety, particularly in dust-prone regions like southern Xinjiang. This study employs high-fidelity computational fluid dynamics (CFD) simulations, combined with the SST turbulence model and the Lagrangian [...] Read more.
As aviation operations extend into complex natural environments, dust particles present significant challenges to flight stability and safety, particularly in dust-prone regions like southern Xinjiang. This study employs high-fidelity computational fluid dynamics (CFD) simulations, combined with the SST turbulence model and the Lagrangian discrete phase model, to analyze the aerodynamic response of the NACA 0012 airfoil at varying wind speeds (5, 15, and 30 m/s) and angles of attack (3°, 8°, and 12°). The results indicate that, at low speeds and moderate to high angles of attack, dust particles reduce lift by over 70%, primarily due to boundary layer instability, weakened suction-side pressure, and premature flow separation. Higher wind speeds slightly delay flow separation, but cannot counteract the disturbances caused by the particles. At higher angles of attack, drag increases by more than 60%, driven by wake expansion, shear dissipation, and delayed pressure recovery. Pitching moment frequently reverses from negative to positive, reflecting a forward shift in the aerodynamic center and a loss of pitching stability. An increase in dust concentration amplifies these effects, leading to earlier moment reversal and more abrupt stall behavior. These findings underscore the urgent need to improve aircraft design, control, and safety strategies for operations in dusty environments. Full article
(This article belongs to the Special Issue Computational Fluid Dynamics for Aerospace and Aeronautical Applications)
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27 pages, 6134 KB  
Article
Research on BPNN-MDSG Hybrid Modeling Method for Full-Cycle Simulation of Surge in Altitude Test Facility Compressor System
by Yang Su, Xuejiang Chen and Xin Wang
Appl. Sci. 2025, 15(15), 8253; https://doi.org/10.3390/app15158253 - 24 Jul 2025
Cited by 1 | Viewed by 937
Abstract
Altitude Test Facility (ATF) compressor systems are widely used in aero-engine tests. These systems achieve the control of gas pressure and transport through complex operation processes. With advancements in the aviation industry, there is a growing demand for higher performance, greater safety, and [...] Read more.
Altitude Test Facility (ATF) compressor systems are widely used in aero-engine tests. These systems achieve the control of gas pressure and transport through complex operation processes. With advancements in the aviation industry, there is a growing demand for higher performance, greater safety, and more energy efficiency in digital ATF systems. Hybrid modeling is a technology that combines many methods and can meet these requirements. The Modular Dynamic System Greitzer (MDSG) compressor model, including mechanistic and data-driven modeling approaches, is combined with a neural network to obtain a BPNN-MDSG hybrid modeling method for the digital turbine system. The digital simulation is linked with the physical sensors of the ATF system to realize real-time simulation and monitoring. The steady and dynamic conditions of the actual system are simulated in virtual space. Compared with the actual results, the average error of steady mass flow is less than 3%, and the error of pressure is less than 1%. The average error of dynamic mass flow is less than 5%, and the error of pressure is less than 3%. The simulation and characteristic predictions are carried out in BPNN-MDSG virtual space. The anti-surge characteristics of the ATF system under start-up conditions are obtained. The full-condition anti-surge operation map of the system is obtained, which provides guidance for the actual operation of the ATF system. Full article
(This article belongs to the Special Issue Computational Fluid Dynamics for Aerospace and Aeronautical Applications)
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