Environmental Influences on Aircraft Aerodynamics

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

Deadline for manuscript submissions: 31 December 2025 | Viewed by 1357

Special Issue Editor


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Guest Editor
College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
Interests: fluid dynamics; aviation and the environment
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Special Issue Information

Dear Colleagues,

Aircraft are flight vehicles that operate in the atmosphere and are thus subject to all kinds of adverse environmental factors such as ice, heavy rain, turbulence, bird flock, volcanic ash, sand and dust. These environmental factors have an influence on the aerodynamics of aircraft. Icing and heavy rain can significantly deteriorate the aerodynamic performance of aircraft by decreasing the lift and increasing the drag, which can further deteriorate the stability and control of the aircraft. Turbulence can cause continuous or intermittent fluctuations in the lift, affecting passengers’ comfort and the structural fatigue of the aircraft. Bird flock is a typical danger to aircraft engines, and can cause engine surges and even flames in the most serious circumstances. In addition, ash, sand and dust are solid particles that are dangerous to aircraft engines, leading to erosion, corrosion and channel clogging. Thus, turboshaft and some advanced turboprop aircraft engines with a bypass duct have been designed to reject foreign objects such as birds, hailstones, ice flakes, sand and dust under the action of the airflow. Of course, the aerodynamic consequences of adverse environments are not fully covered here; therefore, this Special Issue welcomes submissions from aerospace researchers and engineers interested in the airworthiness of aircraft in various environments.

Prof. Dr. Zhenlong Wu
Guest Editor

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Keywords

  • aircraft
  • engine
  • aerodynamics
  • icing
  • heavy rain
  • turbulence
  • bird
  • sand and dust

 

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Published Papers (2 papers)

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Research

18 pages, 28516 KiB  
Article
Aircraft Wing Design Against Bird Strike Using Metaheuristics
by Vanessa Timhede, Silvia Timhede, Seksan Winyangkul and Suwin Sleesongsom
Aerospace 2025, 12(5), 436; https://doi.org/10.3390/aerospace12050436 - 13 May 2025
Viewed by 187
Abstract
Bird strikes pose a significant threat to aviation safety, particularly affecting the wing structures of aircraft. This research aims to design and analyze the impact of bird strikes on wing structures using response surface method and metaheuristics (MHs), which are used to explore [...] Read more.
Bird strikes pose a significant threat to aviation safety, particularly affecting the wing structures of aircraft. This research aims to design and analyze the impact of bird strikes on wing structures using response surface method and metaheuristics (MHs), which are used to explore various risk minimization and damage mitigation techniques. The optimization problem is the minimization of the maximum von Mises stress of aircraft wing structure against bird strike that is subject to displacement and stress constraints. The design variables include skin and rib thickness, as well as sweep angle. Difficulty due to embedded bird strike simulation and optimization design can be alleviated using a response surface method (RSM). The regression technique in the RSM of the data can reach our goal of model fitting with a higher R2 until 0.9951 and 0.9919 are obtained for the displacement and von Mises stress model, respectively. The response surface function of the displacement and von Mises stress are related to skin thickness, while sweep angles rather than rib thickness have a greater impact on both design variables. The optimized design of the design variables is performed using MHs, which are TLBO, JADE, and PBIL. The comparative result of MHs can conclude that the PBIL outperformed others in all descriptive statistics. The optimized design results revealed that the optimum solution can release better energy due to bird strike with the highest limit of skin thickness, moderate rib thickness, and less than half of the sweep angle. The results are in accordance with the response surface function analysis. In conclusion, the optimized design of the aircraft wing structure against bird strike can be accomplished with our proposed technique. Full article
(This article belongs to the Special Issue Environmental Influences on Aircraft Aerodynamics)
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25 pages, 14833 KiB  
Article
Investigation of Flow Control in an Ultra-Compact Serpentine Inlet with Fluidic Oscillators
by Lei Liu, Maolong Bai, Zhihao Wang, Zhengkang Lin, Kun Wang, Huijun Tan and Ziyun Wang
Aerospace 2024, 11(12), 1011; https://doi.org/10.3390/aerospace11121011 - 9 Dec 2024
Viewed by 859
Abstract
For optimal aerodynamic efficiency of specific ultra-compact serpentine intake, fluid oscillators are utilized to regulate airflow. This study employs advanced numerical simulation techniques to examine the effects of various control positions, jet angles, and excitation pressures on flow control efficacy. Control position significantly [...] Read more.
For optimal aerodynamic efficiency of specific ultra-compact serpentine intake, fluid oscillators are utilized to regulate airflow. This study employs advanced numerical simulation techniques to examine the effects of various control positions, jet angles, and excitation pressures on flow control efficacy. Control position significantly impacts the flow field structure within the intake, with a lower surface jet configuration outperforming an upper surface scheme. Optimal performance is achieved with the upper and lower surface jet angles set at 20° and 25°, respectively, under an input pressure of 2.5 times the total inlet pressure. This configuration enhances the total pressure recovery coefficient and reduces the steady-state circumferential distortion index and circumferential total pressure distortion coefficient. However, the flow rate ratio coefficient is notably high. While higher excitation pressures for the fluid oscillator do not inherently exhibit greater effectiveness, careful calibration is essential to accommodate varying positions. Optimal excitation pressure is established for the upper surface, while the control effect on the lower surface improves with increasing excitation pressure. Jet angles significantly affect the fluid oscillator’s control mechanism; small-angle jets effectively add energy to the separation zone, mitigating flow separation, whereas larger jet angles introduce excessive disturbances that outweigh their benefits. Overall, smaller jet angles enhance control effectiveness. Full article
(This article belongs to the Special Issue Environmental Influences on Aircraft Aerodynamics)
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