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New Trends in Applied Aerodynamics
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New Trends in Applied Aerodynamics

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 (10 December 2021) | Viewed by 17473

Special Issue Editor

Dr. Emmanuel P. Bénard

E-Mail Website
Guest Editor
Department of Aerodynamic Energetic and Propulsion, Institut Supérieur de l'Aéronautique et de l'Espace (ISAE), Université de Toulouse, 31000 Toulouse, France
Interests: micro aerial vehicle and unsteady aerodynamics; compressible flows; applied aerodynamics; convective heat transfer; flow/ boundary layer manipulation; collaborative aircraft design; multiphase flows
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear colleagues,

Following more than a century of achievements, and the accumulation of considerable experimental, theoretical and computational knowledge, aerodynamics remains a strong enabler for the development of any sustainable transportation system.  The field of Applied Aerodynamics is now poised with the challenge of defining new horizons, still retaining high efficiency and accuracy characteristics. The aim of this Special Issue of is to foster dissemination of best practice in the field of Applied Aerodynamics and to stimulate ideas exchange in this fast-changing topic. Among the many aspects of the applied aerodynamics field,  original research articles on the state-of-the-art of new methodologies, theoretical, analytical, experimental, and computational tools will be considered (the list not being exhaustive), but works in connected areas are also encouraged: 

  • Challenging physics: separation, laminarity, unsteadiness, from transonics to hypersonics, aeroacoustics, coupled physics…
  • Challenging applications: high angle of attack, rotary wings, ground effects, energy harvesting, strong coupling of aerodynamics and propulsion, low Reynolds number, applied flow-control strategies, bioinspiration, energy harvesting…
  • Impact of emerging methods: machine learning, artificial intelligence, high-fidelity simulations to be run on High Performance Supercomputing (HPC), systems postprocessing data (exergy, far field methods), contribution to “Full digitalization” industry
  • Trade-off and optimization involving aerodynamics: environmental impact, safety, cost, maintenance
  • Education issues in Applied Aerodynamics: foundation and principles for 21st century education in aerodynamics, core topics versus specialized applications, using of combined high fidelity tools and experiments, search of best pedagogical approach versus cost and time, need of updated reference books and media adapted to young generations, impact of open data

Dr. Emmanuel P. Bénard
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

  • Simulation
  • Experimental theory
  • Education
  • Multi-physics
  • Vehicle performance
  • Environmental impact
  • Multi-fidelity
  • Optimization
  • Education

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Published Papers (5 papers)

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Research

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16 pages, 3434 KiB  
Article
Aerodynamic Characteristics of Morphing Supercritical Airfoils for Aircraft with All-Stage High Performance
by Yuwei Cheng, Jinyuan Zeng, Qian Chen, Haizhao Liang and Peng Bai
Appl. Sci. 2022, 12(3), 1128; https://doi.org/10.3390/app12031128 - 21 Jan 2022
Cited by 3 | Viewed by 2927
Abstract
Morphing airfoil is a promising technology for future aircraft to realize all-stage high performance. In the present paper, a conceptual aircraft with morphing airfoil is proposed and the aerodynamic characteristics of three types of morphing airfoils (variable-camber airfoil, variable-chord airfoil, and the combination [...] Read more.
Morphing airfoil is a promising technology for future aircraft to realize all-stage high performance. In the present paper, a conceptual aircraft with morphing airfoil is proposed and the aerodynamic characteristics of three types of morphing airfoils (variable-camber airfoil, variable-chord airfoil, and the combination of both morphing styles) are numerically investigated. The baseline airfoil is RAE 2822 supercritical airfoil; the Reynolds-averaged Navier–Stokes method is adopted for numerical simulation of flow around airfoils, and the accuracy of the numerical simulation method is validated by comparing with experimental data. It is found that the variable-camber and -chord airfoil can not only improve the high lift characteristics at take-off stage, but also increase the lift-to-drag ratio at transonic cruise and low-speed task stages during which the required lift is continuously decreasing due to the consumption of fuel. These findings imply that aircraft with proper morphing airfoil can achieve all-stage high aerodynamic performance. Full article
(This article belongs to the Special Issue New Trends in Applied Aerodynamics)
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19 pages, 9893 KiB  
Article
Numerical Analysis of the Take-Off Performance of a Seaplane in Calm Water
by Yang Guo, Dongli Ma, Muqing Yang and Xing’an Liu
Appl. Sci. 2021, 11(14), 6442; https://doi.org/10.3390/app11146442 - 13 Jul 2021
Cited by 5 | Viewed by 3397
Abstract
Nowadays, with the escalating tensions in maritime dispute and the development of marine economy, there has been renewed interest in seaplanes for their special capacity of taking off and landing on water. Prediction of take-off performance, involving aerodynamic analysis and hydrodynamic analysis, is [...] Read more.
Nowadays, with the escalating tensions in maritime dispute and the development of marine economy, there has been renewed interest in seaplanes for their special capacity of taking off and landing on water. Prediction of take-off performance, involving aerodynamic analysis and hydrodynamic analysis, is a main challenge in seaplane design, while the prediction methods have been little improved since the 1960s. This paper aims to investigate the attitude and resistance characteristics of a seaplane at different speeds during the take-off by numerically modeling the air-water flow field using RANS equations with VOF method. The trim and heave motion of seaplane in response to aerodynamic forces, hydrodynamic forces, hydrostatic forces, and propeller thrust was realized by solving rigid body dynamics equations and adopting dynamic overset mesh technique. The variations in heave, trim angle, and resistance characteristics during the takeoff were investigated, and their inherent relationships with the aerodynamic, hydrodynamic, and hydrostatic performance were revealed. Particular investigation on the hydrodynamic resistance indicates that the stagnation line located at the convex bow would contribute a considerable increase of pressure resistance at the first hump, and the trim angel of a seaplane should be operated in an optimum trim range, typical between 4–6 deg, to minimize the hydrodynamic resistance at the second hump. Additionally, the dynamic motion convergence study proves that the utilization of damping terms was an effective way to accelerate the convergence of the dynamic motion ending with a quasi-static state. Full article
(This article belongs to the Special Issue New Trends in Applied Aerodynamics)
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19 pages, 9303 KiB  
Article
Numerical Study on Airfoil Aerodynamics in Proximity to Wavy Water Surface for Various Amplitudes
by Xing’an Liu, Dongli Ma, Muqing Yang, Yang Guo and Haode Hu
Appl. Sci. 2021, 11(9), 4215; https://doi.org/10.3390/app11094215 - 6 May 2021
Cited by 2 | Viewed by 2894
Abstract
Wing–in–ground crafts will face waves with different amplitudes when flying over the ocean, and the high amplitude situations are especially lack of exploration. Hence, the aerodynamic characteristics of the NACA 4412 airfoil in proximity to the wavy water surface for various wave amplitudes [...] Read more.
Wing–in–ground crafts will face waves with different amplitudes when flying over the ocean, and the high amplitude situations are especially lack of exploration. Hence, the aerodynamic characteristics of the NACA 4412 airfoil in proximity to the wavy water surface for various wave amplitudes are inspected in this paper. By solving Navier–Stokes equations, the lift coefficients of the airfoil when the angle of attack ranges from 0° to 4° are obtained. The results show that the fluctuation amplitudes of aerodynamic coefficients increase remarkably with successive increases in the wave amplitude and might threaten flight safety. The flow fields at 0° with low and high wave amplitudes are investigated. It is revealed that the upward movement of the water surface is the critical factor for the change of aerodynamics, and the mechanism varies with different wave amplitudes. Comparison of the flow fields at 0° and 2° further indicates that the influence of high amplitude waves depends on the distance between the leading edge of the airfoil and the water surface. This study discovers the reasons for the different aerodynamic characteristics under various wave amplitudes and angles of attack, and is of great value for the design of wing–in–ground crafts. Full article
(This article belongs to the Special Issue New Trends in Applied Aerodynamics)
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20 pages, 30190 KiB  
Article
Estimation of Aircraft-Dependent Bumpiness Severity in Turbulent Flight
by Haofeng Wang, Zhenxing Gao, Hongbin Gu and Kai Qi
Appl. Sci. 2021, 11(4), 1796; https://doi.org/10.3390/app11041796 - 18 Feb 2021
Cited by 1 | Viewed by 2192
Abstract
Atmospheric turbulence threatens flight safety of civil aviation aircraft by inducing aircraft bumpiness. A severity estimation method of aircraft bumpiness in turbulent flight is explored according to in-situ Eddy Dissipation Rate (EDR) indicator. With the turbulence intensity derived from EDR value, a time [...] Read more.
Atmospheric turbulence threatens flight safety of civil aviation aircraft by inducing aircraft bumpiness. A severity estimation method of aircraft bumpiness in turbulent flight is explored according to in-situ Eddy Dissipation Rate (EDR) indicator. With the turbulence intensity derived from EDR value, a time series of longitudinal and vertical turbulence was generated according to von Karman turbulence model. In order to obtain the vertical acceleration response of aircraft, the continuous change of aerodynamic force on the assembly of wing and horizontal tail was computed by Unsteady Vortex Lattice Method (UVLM). The computing accuracy was improved by using semi-circle division and assigning the vortex rings on the mean camber surface. Furthermore, the adverse effects of control surface deflections on bumpiness severity estimation can be effectively removed by separating turbulence-induced and aircraft maneuvers-induced aerodynamic force change. After that, the variance of vertical acceleration, as the severity indicator of aircraft bumpiness, was obtained by Welch spectrum estimation. With the refined grid level, the pitching moment change due to control surface deflections can be solved accurately by UVLM. The instantaneous acceleration change obtained by UVLM approximates recorded acceleration data with better accuracy than linear transfer function model. A further test with a set of flight data on the same airway shows that compared with in-situ EDR indicator, the proposed method gives an aircraft-dependent estimation of bumpiness severity, which can not only be used to estimate in-situ bumpiness but also be applied to forecast the bumpiness severity of other different aircrafts. Full article
(This article belongs to the Special Issue New Trends in Applied Aerodynamics)
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Review

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22 pages, 3193 KiB  
Review
Passive Control of Base Pressure: A Review
by Ambareen Khan, Parvathy Rajendran and Junior Sarjit Singh Sidhu
Appl. Sci. 2021, 11(3), 1334; https://doi.org/10.3390/app11031334 - 2 Feb 2021
Cited by 13 | Viewed by 4384
Abstract
In the present world, passive control finds application in various areas like flow over blunt projectiles, missiles, supersonic parallel diffusers (for cruise correction), the engine of jets, static testbeds of rockets, the ports of internal combustion engines, vernier rockets, and single expansion ramp [...] Read more.
In the present world, passive control finds application in various areas like flow over blunt projectiles, missiles, supersonic parallel diffusers (for cruise correction), the engine of jets, static testbeds of rockets, the ports of internal combustion engines, vernier rockets, and single expansion ramp nozzle (SERN) rockets. In this review, various passive control techniques to control the base pressure and regulate the drag force are discussed. In the study, papers ranging from subsonic, sonic, and supersonic flow are discussed. Different types of passive control management techniques like cavity, ribs, dimple, static cylinder, spikes, etc., are discussed in this review article. This study found that the passive control device can control the base pressure, resulting in an enhancement in the base pressure and reducing the base drag. Also, passive control is very efficient whenever there is a favorable pressure gradient at the nozzle exit. Full article
(This article belongs to the Special Issue New Trends in Applied Aerodynamics)
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