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Aerodynamics and Aeroacoustics
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Aerodynamics and Aeroacoustics

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

Deadline for manuscript submissions: closed (28 February 2023) | Viewed by 7867

Special Issue Editor

Prof. Dr. Yijun Mao

E-Mail Website
Guest Editor
School of Aerospace Engineering, Huazhong University of Science and Technology, Wuhan 430074, China
Interests: turbomachinery flow and noise
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

Aerodynamics and aeroacoustics are critical topics in various engineering applications, such as airplanes, automobiles, high-speed trains, turbomachines and HVAC systems. This Special Issue focuses on the fundamental and applied aspects of aerodynamics and aeroacoustics and calls for high-quality papers in the fields of theoretical, experimental, and numerical advances in aerodynamics and aeroacoustics.

A non-exhaustive list of topics follows:

  • Analytical methods in aerodynamics and aeroacoustics;
  • Computational fluid dynamics and computational aeroacoustics;
  • Experimental techniques of aerodynamics and aeroacoustics;
  • Flow and noise control;
  • Jet flow and noise;
  • Rotor flow and noise;
  • Turbomachinery flow and noise;
  • Acoustics of multiphase/multicomponent flow and combustion noise.

Prof. Dr. Yijun Mao
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 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. 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

  • aerodynamics
  • unsteady flow
  • aeroacoustics
  • aerodynamic noise

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Published Papers (2 papers)

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Research

22 pages, 21695 KiB  
Article
A Numerical Analysis of Active Flow Control Techniques for Aerodynamic Drag Reduction in the Square-Back Ahmed Model
by Thanh-Long Phan, Quoc Thai Pham, Thi Kim Loan Nguyen and Tien Thua Nguyen
Appl. Sci. 2023, 13(1), 239; https://doi.org/10.3390/app13010239 - 25 Dec 2022
Cited by 7 | Viewed by 3267
Abstract
Aerodynamic drag reduction is required with new stringent constraints on pollutant emissions and fuel efficiency of ground vehicles. In this context, active flow control is a promising approach to achieve this target. This study focuses on applying different flow control strategies on the [...] Read more.
Aerodynamic drag reduction is required with new stringent constraints on pollutant emissions and fuel efficiency of ground vehicles. In this context, active flow control is a promising approach to achieve this target. This study focuses on applying different flow control strategies on the square-back Ahmed model to reduce aerodynamic drag. A steady blowing jet, a synthetic jet and an unsteady jet are located at the back edges of the model as flow control devices. A numerical study based on the 3D WMLES simulation was performed to evaluate the drag reduction capabilities of these devices at different operating conditions. The results showed that a maximum aerodynamic drag reduction of 26.51% was achieved when using a steady blowing jet, and 17.27% with an unsteady jet. In contrast, the effect of the synthetic jet on the aerodynamic drag of the model is solely at high control frequencies. Full article
(This article belongs to the Special Issue Aerodynamics and Aeroacoustics)
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21 pages, 12542 KiB  
Article
Investigation and Design of the Transonic Laminar Flow Characteristics in a Laminar Aircraft
by Xiaotian Niu and Jie Li
Appl. Sci. 2022, 12(22), 11820; https://doi.org/10.3390/app122211820 - 21 Nov 2022
Cited by 2 | Viewed by 3747
Abstract
Reducing drag is critical to aircraft design. In recent years, laminar technology has become one of the most important feasible technologies for civil aircraft drag reduction design under many design constraints. However, various factors have a certain impact on the laminar flow characteristics [...] Read more.
Reducing drag is critical to aircraft design. In recent years, laminar technology has become one of the most important feasible technologies for civil aircraft drag reduction design under many design constraints. However, various factors have a certain impact on the laminar flow characteristics in the state of transonic flight. Therefore, it is necessary to deeply understand the specific effects of various flight parameters on the characteristics of laminar flow. In this paper, a parameter sensitivity analysis for a central experimental wing in a special layout aircraft was carried out to investigate its transonic laminar characteristics. Then, the airfoil of the central experimental wing of the aircraft was designed for real flight. The RANS (Reynold-averaged Navier–Stokes) method combined with the γ−Reθ transition model based on local variables was used. The computational approach was validated by the wind tunnel tests and analyzed by the grid independence analysis. The sensitivity mainly focuses on the transition location and the length of the laminar flow zone of the central experiment under different boundary conditions. The transonic transition was affected by a variety of interacting factors that include FSTI (free stream turbulence intensity), pressure gradient, Re (Reynolds number), Ma (Mach number) and α (angle of attack, degree). The essence of the transition is the disruption of flow stability caused by the increase in flow entropy. Among these factors, FSTI directly affects global flow stability, and the pressure gradient affects local flow stability. Ma and α can indirectly affect the flow stability by changing the pressure gradient. Re can control the boundary layer properties to change the flow stability, whereas its effect is easily determined by the pressure gradient. Finally, the improved design of the airfoil with the central experimental wing was conducted. The design of weak shock wave and aerodynamic load on the rear part of the airfoil can improve the aerodynamic characteristics (CL, lift coefficient, increases by 0.28) of the airfoil, which can reduce the load burden on the outboard wing without affecting the laminar flow characteristics of the airfoil. In the next step, cross-flow instability will be considered. Full article
(This article belongs to the Special Issue Aerodynamics and Aeroacoustics)
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