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Aerospace
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Aerodynamics and Aeroacoustics of Unsteady Flow
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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 1040

Special Issue Editors

Dr. Teng Zhou

E-Mail Website
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
Dr. Wangqiao Chen

E-Mail Website
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
Dr. Jingwen Guo

E-Mail Website
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

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. 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

  • 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 (2 papers)

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Research

15 pages, 11215 KiB  
Article
Effects of Reduced Frequency on the Aerodynamic Characteristics of a Pitching Airfoil at Moderate Reynolds Numbers
by Teng Zhou, Huijing Cao and Ben Zhao
Aerospace 2025, 12(6), 457; https://doi.org/10.3390/aerospace12060457 - 23 May 2025
Abstract
Aerodynamic characteristics of a pitching NACA 0012 airfoil, including the load performance and flow field features, are studied using numerical simulations in this paper. Large Eddy Simulations (LESs) have been performed, and the chord-based Reynolds number is set to 6.6×104 [...] Read more.
Aerodynamic characteristics of a pitching NACA 0012 airfoil, including the load performance and flow field features, are studied using numerical simulations in this paper. Large Eddy Simulations (LESs) have been performed, and the chord-based Reynolds number is set to 6.6×104. Pitching frequency varies from 3 to 20 Hz, corresponding to a reduced frequency of 0.094–0.628 (k=πfpc/U∞, where fp is the pitching frequency, c is the chord length, and U∞ refers to the incident flow speed). As the pitching frequency increases, the maximum lift coefficient achieved in one pitching cycle decreases, and the direction of the lift hysteresis loop changes as the pitching frequency exceeds a certain value, leading to a change in the lift of the sign at the zero-incidence moment, which is a result of the instantaneous flow patterns on the airfoil surface. As the pitching frequency increases, flow unsteadiness develops less in one pitching cycle, and the time duration in which the turbulence boundary layer can be detected in one pitching cycle shrinks. Additionally, for the pitching airfoil, combinations of the flow patterns on the upper and lower sides, such as laminar separation and the turbulent boundary layer, or laminar separation and the laminar separation bubble, were observed on the airfoil surface, and these were not detected on a static airfoil at the corresponding Reynolds number. This is considered an effect of the pitching motion that is in addition to the phase-lag effect. Full article
(This article belongs to the Special Issue Aerodynamics and Aeroacoustics of Unsteady Flow)
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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 697
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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