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Aerospace
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Large Eddy Simulation in Aerospace Engineering
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Large Eddy Simulation in Aerospace Engineering

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

Deadline for manuscript submissions: closed (15 November 2021) | Viewed by 15235

Special Issue Editor

Prof. Dr. Andreas Gross

E-Mail Website
Guest Editor
Mechanical and Aerospace Engineering Department, New Mexico State University, Las Cruces, NM 88003, USA
Interests: computational fluid dynamics; direct numerical simulations; large eddy simulations; hybrid turbulence modeling; flow control; chemical non-equilibrium flows; high-performance computing; unmanned aerial vehicles; renewable energy

Special Issue Information

Dear Colleagues,

The idea of the numerical wind tunnel, which allows for the virtual testing of entire aerospace vehicles, is intriguing and has motivated research and development in numerical methods, turbulence modeling, and hardware architecture among others. Although direct numerical simulations of full-size aerospace vehicles will remain out of reach for the foreseeable future, large-eddy simulations promise to break into the realm of design and analysis, which has long been dominated by Reynolds-averaged Navier–Stokes simulations. Large-eddy simulations are already providing the basis for a large number of significant contributions to many areas of science broadly associated with turbulent transport phenomena. This Special Issue aims to document the state-of-the-art in large-eddy simulations for aerospace applications. Articles are sought that are representative of today’s capability of large-eddy simulations, that summarize recent developments in sub-grid stress and wall modeling, and that make projections about the future potential of large-eddy simulations and the anticipated computing and storage requirements.

Prof. Dr. Andreas Gross
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. 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

  • large-eddy simulation
  • aerodynamic analysis
  • sub-grid stress modelling
  • wall-modeling
  • future trends in large-eddy simulation

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Published Papers (4 papers)

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Research

16 pages, 5751 KiB  
Article
An Improved Synthetic Eddy Method for Generating Inlet Turbulent Boundary Layers
by Dapeng Xiong, Yinxin Yang and Yanan Wang
Aerospace 2022, 9(1), 37; https://doi.org/10.3390/aerospace9010037 - 13 Jan 2022
Cited by 4 | Viewed by 2461
Abstract
An improved synthetic eddy method (SEM) is proposed in this paper for generating the boundary layer at the inlet of a computational domain via direct numerical simulation. The improved SEM modified the definition of the radius and the velocities of the eddies according [...] Read more.
An improved synthetic eddy method (SEM) is proposed in this paper for generating the boundary layer at the inlet of a computational domain via direct numerical simulation. The improved SEM modified the definition of the radius and the velocities of the eddies according to the distance of the eddies from the wall in the synthetic region. The regeneration location of the eddies is also redefined. The simulation results show that the improved SEM generates turbulent fluctuations that closely match the DNS results of the experiments. The skin friction coefficient of the improved SEM recovers much faster and has lower dimensionless velocity at the outer of the boundary layer than that of the traditional SEM. Full article
(This article belongs to the Special Issue Large Eddy Simulation in Aerospace Engineering)
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20 pages, 9407 KiB  
Article
Dynamic Burst Actuation to Enhance the Flow Control Authority of Plasma Actuators
by Takuto Ogawa, Kengo Asada, Satoshi Sekimoto, Tomoaki Tatsukawa and Kozo Fujii
Aerospace 2021, 8(12), 396; https://doi.org/10.3390/aerospace8120396 - 13 Dec 2021
Cited by 10 | Viewed by 3401
Abstract
A computational study was conducted on flows over an NACA0015 airfoil with dielectric barrier discharge (DBD) plasma. The separated flows were controlled by a DBD plasma actuator installed at the 5% chord position from the leading edge, where operated AC voltage was modulated [...] Read more.
A computational study was conducted on flows over an NACA0015 airfoil with dielectric barrier discharge (DBD) plasma. The separated flows were controlled by a DBD plasma actuator installed at the 5% chord position from the leading edge, where operated AC voltage was modulated with the duty cycle not given a priori but dynamically changed based on the flow fluctuations over the airfoil surface. A single-point pressure sensor was installed at the 40% chord position of the airfoil surface and the DBD plasma actuator was activated and deactivated based on the strength of the measured pressure fluctuations. The Reynolds number was set to 63,000 and flows at angles of attack of 12 and 16 degrees were considered. The three-dimensional compressible Navier–Stokes equations including the DBD plasma actuator body force were solved using an implicit large-eddy simulation. Good flow control was observed, and the burst frequency proven to be effective in previous fixed burst frequency studies is automatically realized by this approach. The burst frequency is related to the characteristic pressure fluctuation; our approach was improved based on the findings. This improved approach realizes the effective burst frequency with a lower control cost and is robust to changing the angle of attack. Full article
(This article belongs to the Special Issue Large Eddy Simulation in Aerospace Engineering)
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19 pages, 2260 KiB  
Article
Statistical Analysis of Dynamic Subgrid Modeling Approaches in Large Eddy Simulation
by Mohammad Khalid Hossen, Asokan Mulayath Variyath and Jahrul M. Alam
Aerospace 2021, 8(12), 375; https://doi.org/10.3390/aerospace8120375 - 3 Dec 2021
Cited by 8 | Viewed by 2932
Abstract
In large eddy simulation (LES) of turbulent flows, dynamic subgrid models would account for an average cascade of kinetic energy from the largest to the smallest scales of the flow. Yet, it is unclear which of the most critical dynamical processes can ensure [...] Read more.
In large eddy simulation (LES) of turbulent flows, dynamic subgrid models would account for an average cascade of kinetic energy from the largest to the smallest scales of the flow. Yet, it is unclear which of the most critical dynamical processes can ensure the criterion mentioned above. Furthermore, evidence of vortex stretching being the primary mechanism of the cascade is not out of the question. In this article, we study essential statistical characteristics of vortex stretching. Our numerical results demonstrate that vortex stretching rate provides the energy dissipation rate necessary for modeling subgrid-scale turbulence. We have compared the interaction of subgrid stresses with the filtered quantities among four models using invariants of the velocity gradient tensor. The individual and the joint probability of vortex stretching and strain amplification show that vortex stretching rate is highly correlated with the energy cascade rate. Sheet-like flow structures are correlated with viscous dissipation, and vortex tubes are more stretched than compressed. The overall results indicate that the stretching mechanism extracts energy from the large-scale straining motion and passes it onto small-scale stretched vortices. Full article
(This article belongs to the Special Issue Large Eddy Simulation in Aerospace Engineering)
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28 pages, 38156 KiB  
Article
Large-Eddy Simulation of Low-Pressure Turbine Cascade with Unsteady Wakes
by Zachary Robison and Andreas Gross
Aerospace 2021, 8(7), 184; https://doi.org/10.3390/aerospace8070184 - 8 Jul 2021
Cited by 9 | Viewed by 3314
Abstract
To better understand the wake effects at low Reynolds numbers, large-eddy simulations of a 50% reaction low-pressure turbine stage and a linear cascade with two different bar wake generators were carried out for a chord Reynolds number of 50,000. For the chosen front-loaded [...] Read more.
To better understand the wake effects at low Reynolds numbers, large-eddy simulations of a 50% reaction low-pressure turbine stage and a linear cascade with two different bar wake generators were carried out for a chord Reynolds number of 50,000. For the chosen front-loaded high-lift airfoil, the endwall structures are stronger than for more traditional mid-loaded moderate-lift airfoils. By comparing the 50% reaction stage results with the bar wake generator results, insight is gained into the effect of the three-dimensional wake components on the downstream flow field.For the cases with bar wake generator, the endwall boundary layer is growing faster because of the relative motion of the endwall with respect to the freestream. The half-width of the wake is approximately matched for the larger one of the two considered bar wake generators. To improve the quality of the phase-averaged flow fields, the proper orthogonal decomposition was employed as a filter to remove the low-energy unsteady flow field content. Both the mean flow and filtered phase-averaged flow fields were analyzed in detail. Visualizations of the phase-averaged flow field reveal a periodic suppression of the laminar suction side separation from the downstream airfoil even for the smaller bar wake generator. The passage vortex is entirely suppressed for the 50% reaction stage and for the larger bar wake generator. Furthermore, the phase-averaged data for the 50% reaction stage reveal a new longitudinal flow structure that is traced back to near-wall wake vorticity. This flow structure is missing for the bar wake generator cases. Full article
(This article belongs to the Special Issue Large Eddy Simulation in Aerospace Engineering)
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