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Aerospace
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Recent Advances in Applied Aerodynamics (2nd Edition)
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Recent Advances in Applied Aerodynamics (2nd Edition)

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

Deadline for manuscript submissions: 28 February 2026 | Viewed by 2632

Special Issue Editor

Prof. Dr. Cheolheui Han

E-Mail Website
Guest Editor
Department of Aeronautical and Mechanical Design Engineering, Korea National University of Transportation, Chungju-si 27496, Republic of Korea
Interests: low-speed aerodynamics; unsteady aerodynamics; formation flight; wing-in-ground effect aircraft design; biomimetics
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

Applied aerodynamics seeks to understand and utilize the fundamental aspects of fluid flow in the analysis, design, and integration of aerodynamic geometries. This field covers a broad range of applications, generally involving any object that experiences aerodynamic forces in fluid flow, though common applications include fixed-wing or rotary-wing aircraft, wind turbines and propellers, ground and marine vehicles, internal flows, avian and insect flight, and atmospheric flows. We are seeking papers on theoretical, experimental, and computational approaches to aerodynamics applications. Areas of interest include, but are not limited to, flight or ground vehicle aerodynamic design, the analysis of wing/rotor/vehicle aerodynamic performance, methods for modeling aerodynamic bodies, and novel studies or technological applications related to aerodynamic applications. Specific areas of interest are listed below but work in related areas is also encouraged.

  • Aerodynamic design: Analysis, methodologies, and optimization techniques;
  • Aerodynamic flow control: Analytical, computational, and experimental;
  • Aerodynamic testing: Ground, wind tunnel, and flight testing;
  • Aero-propulsive interactions and aerodynamics of integrated propeller systems;
  • Airfoil/wing/configuration aerodynamics;
  • Applied aeroelasticity and aerodynamic–structural dynamics interaction;
  • Applied computational fluid dynamics;
  • Boundary layer transition for aerodynamic applications;
  • CFD methods for aerodynamics applications;
  • Propeller/rotorcraft/wind turbine aerodynamics;
  • Reduced-order aerodynamics modeling and system identification;
  • Transonic and supersonic aerodynamics;
  • Unsteady aerodynamics and massively separated flows.

Prof. Dr. Cheolheui Han
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 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. 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 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

  • CFD
  • aerodynamic testing
  • design optimization
  • flow control
  • flow–structure interaction
  • boundary layer transition

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

Related Special Issue

Published Papers (3 papers)

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Research

32 pages, 19883 KB  
Article
Enabling Sustainable After-Market Aircraft Electrification: Aerodynamic Impact of High-Performance Battery Cooling Ports
by Mark Hargreaves, Dean Koumakis, Keith Joiner and Dylan D. Dooner
Aerospace 2025, 12(12), 1053; https://doi.org/10.3390/aerospace12121053 - 26 Nov 2025
Viewed by 288
Abstract
The transition to electric aircraft for zero-emission transport requires integrating thermal management systems for high-performance batteries without incurring significant weight, balance, or aerodynamic penalties. This study focuses on the aerodynamic penalties associated with air-cooling systems that can compound the presently unavoidable reduction in [...] Read more.
The transition to electric aircraft for zero-emission transport requires integrating thermal management systems for high-performance batteries without incurring significant weight, balance, or aerodynamic penalties. This study focuses on the aerodynamic penalties associated with air-cooling systems that can compound the presently unavoidable reduction in endurance imposed by current battery energy density limitations. Building on previous research into battery installation layouts and internal cooling flows, this study is the first to investigate the lift-to-drag (L/D) optimisation for the multiple wing-mounted inlets and outlets necessary for air-cooling batteries in the wing of an electrified aircraft. Wing leading-edge inlets and NACA (National Advisory Committee for Aeronautics) ducts were analysed by systematically varying their layout, number, and dimensions. The analysis evaluated their effects on the wing’s lift, drag, and moment to maximise the L/D. Multiple highly efficient simulation test designs were developed to screen for the main factors to identify the best inlet and outlet configuration, resulting in 66 different Computational Fluid Dynamics (CFD) simulations in Ansys Fluent. Following this, three CFD verification cases of the best configuration were conducted to verify the cooling effect by combining both internal and external flow simulations with heat generation. Compared to the baseline wing of the carbon combustion aircraft, the best configuration caused a 1.75% reduction in L/D, range, and endurance. While the aerodynamic penalty is now minimised, the internal battery pack layout requires further optimisation to re-establish uniform cooling across the battery pack. Designers may still be able to separate the CFD analysis of the internal and external flow regimes with idealised inlets and outlets; however, more whole-field CFD iterations are needed to guide such subdivision to a viable and safe design for wing-mounted batteries. Further, the margins are such that wing-mounted electrification warrants careful instrumented validation in an aircraft. These findings provide crucial design guidance for sustainable aviation, particularly to enable after-market electrification projects. Full article
(This article belongs to the Special Issue Recent Advances in Applied Aerodynamics (2nd Edition))
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19 pages, 3793 KB  
Article
Assessment of Oscillating Wings to Deliver Air Mass Flow Under Power and Thrust Constraints
by Emin Burak Ozyilmaz and Mustafa Kaya
Aerospace 2025, 12(8), 740; https://doi.org/10.3390/aerospace12080740 - 20 Aug 2025
Viewed by 729
Abstract
An oscillating wing was evaluated for its ability to deliver air mass flow. The evaluation was based on exploring the oscillation parameters that provide a given mass flow rate at the least power requirement with the highest possible thrust generation. Wing oscillation was [...] Read more.
An oscillating wing was evaluated for its ability to deliver air mass flow. The evaluation was based on exploring the oscillation parameters that provide a given mass flow rate at the least power requirement with the highest possible thrust generation. Wing oscillation was defined as coupled pitch and plunge motions. The support vector regression algorithm was implemented as a machine learning tool to link the oscillation parameters to power and thrust values. The required power and generated thrust values were computed by solving the unsteady turbulent flows around the wings. The results were also compared to the performance of an axial flow fan that delivered the same amount of air mass flow. It was found that an oscillating wing is compatible with an axial fan in terms of power requirement and thrust generation. Full article
(This article belongs to the Special Issue Recent Advances in Applied Aerodynamics (2nd Edition))
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18 pages, 4564 KB  
Article
Multi-Fidelity Modeling of Isolated Hovering Rotors
by Jason Cornelius, Nicholas Peters, Tove Ågren and Hugo Hjelm
Aerospace 2025, 12(8), 650; https://doi.org/10.3390/aerospace12080650 - 22 Jul 2025
Viewed by 1151
Abstract
Surrogate modeling has been rapidly evolving in the field of aerospace engineering, further reducing the cost of computational analyses. These models often require large amounts of information to learn the underlying process, which is at odds with obtaining and using the highest-fidelity data. [...] Read more.
Surrogate modeling has been rapidly evolving in the field of aerospace engineering, further reducing the cost of computational analyses. These models often require large amounts of information to learn the underlying process, which is at odds with obtaining and using the highest-fidelity data. This study assesses the efficacy of multi-fidelity modeling (MFM) to improve simulation accuracy while reducing computational cost. A database of hovering rotor simulations with perturbations of the rotor design and operating conditions was first generated using two different fidelity levels of the OVERFLOW 2.4D Computational Fluid Dynamics software. MFM was then used to quantify the effectiveness of this approach for the development of accurate surrogate models. Multi-fidelity models based on Gaussian Process Regression (GPR) were derived for hovering rotor performance prediction given the geometric rotor blade inputs that currently include twist, planform, airfoil, and the collective pitch angle. The MFM approach was consistently more accurate at predicting the hold-out test data than the surrogate model with high-fidelity data alone. An MFM using just 20% of the available high-fidelity training data was as accurate as a solely high-fidelity model trained on 80% of the available data, representing an approximate fourfold reduction in computational cost. Full article
(This article belongs to the Special Issue Recent Advances in Applied Aerodynamics (2nd Edition))
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