Aerodynamics and Aeroacoustics of Unsteady Flow

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

Deadline for manuscript submissions: 30 September 2025 | Viewed by 524

Special Issue Editors


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Guest Editor
Institute of Sound and Vibration Research, University of Southampton, Southampton SO17 1BJ, UK
Interests: aeroacoustics and aerodynamics of dynamic stall; rotor noise; centrifugal compressor noise

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Guest Editor
Department of Mechanical and Aerospace Engineering, The Hong Kong University of Science and Technology, Hong Kong SAR, China
Interests: transient analysis of airfoil and rotor trailing edge noise; super-resolution acoustic imaging method; wave turbulence theory in nonlinear acoustics; ultra-low frequency parametric array

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Guest Editor
Institute of Acoustics Chinese Academy of Sciences, Beijing 100190, China
Interests: aeroacoustics; noise control; high-accuracy numerical simulation; machine learning

Special Issue Information

Dear Colleagues,

This Special Issue of Aerospace covers recent research outcomes concerning aerodynamic structures, including aircraft airfoils/wings, high-lift structures, propeller blades, and compressor/rotor blades. The complex flow physics and aeroacoustics of these configurations pose significant challenges in both experimental and numerical studies, including three-dimensional unsteady flow structures, the combined effect of rotational augmentation and dynamic stall, the physics of leading/trailing-edge noise generation, and the high-accuracy prediction of aerodynamic noise and low-noise designs.

An additional topic of interest in this Special Issue is the interaction between flow and structures. As unmanned aerial vehicles have seen rapid recent development, the interactions between multiple rotors or between rotor and structures have attracted increasing attention. Some essential problems, including the unsteady loading induced by the rotor–wake interaction, the noise induced by the interaction between turbulence and blade, transient noise identification in multiple rotor system, etc., are yet to be investigated. The editors of this Special Issue invite authors to submit papers addressing the challenges in experimental and numerical studies of the aerodynamics and aeroacoustics of unsteady flow problems.

Dr. Teng Zhou
Dr. Wangqiao Chen
Dr. Jingwen Guo
Guest Editors

Manuscript Submission Information

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Keywords

  • computational fluid dynamics
  • unsteady flow
  • rotor–rotor interaction
  • fluid structure interaction
  • experimental aerodynamics/aeroacoustics
  • computational aeroacoustics
  • wing noise
  • rotor noise

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Published Papers (1 paper)

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Research

22 pages, 24655 KiB  
Article
Numerical Analyses of Aerodynamic and Aeroacoustic Interaction Characteristics of Rear-Mounted Propeller on Highspeed Helicopter
by Dazhi Sun, Xi Chen, Qijun Zhao and Weicheng Bao
Aerospace 2025, 12(4), 343; https://doi.org/10.3390/aerospace12040343 - 15 Apr 2025
Viewed by 236
Abstract
To study the interference effects of the fuselage/rear-mounted propeller on the aerodynamic and aeroacoustic characteristics at a forward speed of Ma = 0.323, a multi-component flowfield simulation and an aeroacoustic prediction method were employed. Firstly, hybrid grids were adopted in the embedded grid [...] Read more.
To study the interference effects of the fuselage/rear-mounted propeller on the aerodynamic and aeroacoustic characteristics at a forward speed of Ma = 0.323, a multi-component flowfield simulation and an aeroacoustic prediction method were employed. Firstly, hybrid grids were adopted in the embedded grid system, and a new boundary identification method was developed to address the overlap problem by adjusting the grid boundary based on entities. The simulations were based on the URANS and FW-H equations. The employed numerical analysis methods were validated through comparisons with experimental data. Then, the aerodynamic and aeroacoustic characteristics of the propeller were analyzed, and the interference of the fuselage with the propeller was discussed in detail. Key findings included the following. Under fuselage interference, the sound pressure level (SPL) of the propeller at those observers near the forward flight direction increased dramatically, by more than 10 dB, especially in the range of two to six times the fundamental frequency. A downward vertical velocity reduced the SPLs beneath the fuselage, while an upward one had the opposite effect. The flat/vertical tails’ deceleration effect caused a thrust surge in the propeller, with most magnitudes around 20%. At different forward speeds, the thrust surge and SPL changes were similar. Full article
(This article belongs to the Special Issue Aerodynamics and Aeroacoustics of Unsteady Flow)
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