Special Issue "Physics-based, High-Fidelity Computational modelling for Aerospace Application"

A special issue of Aerospace (ISSN 2226-4310).

Deadline for manuscript submissions: closed (31 July 2021) | Viewed by 4105

Special Issue Editors

Faculty of Engineering and Physical Sciences, University of Southampton, Southampton SO171BJ, UK
Interests: aerodynamics; structures; aeroelasticity; model reduction; control
Special Issues, Collections and Topics in MDPI journals
School of Engineering, Zurich University of Applied Sciences, 8400 Winterthur, Switzerland
Interests: aeroelasticity; unsteady aerodynamics; aeroacoustics; turbulence modelling

Special Issue Information

Dear colleagues,

A remarkable progress in computational multi-physics and multi-disciplinary aero-sciences has been achieved over the last two decades, driven by the rightful decision to reduce the footprint of aviation on the environment and to improve the well-being of the communities situated around airports. This Special Issue wants to provide the current state-of-the-art in the development and deployment of high-fidelity computational methods for the analysis and simulation of aerospace vehicles by collecting multi-faceted contributions in key areas, such as: the analysis of low-speed stall, the appearance and evolution of stall cells for clean and take-off/landing wing configurations; characterization of flow separations and turbulent structures, (identification of) noise sources and dynamic loads for slats/flats installations and landing gear configurations; ice accretion and the impact of icing on the vehicle performances; the interactions between the propulsive system and the airframe, with associated thermal, acoustic, fatigue and radar cross-section issues; off-design conditions, including buffeting and fluid-structure interaction problems during gust encounters and manoeuvres. Hybrid RANS-LES turbulence modelling techniques such as DDES, IDDES, ZDES, WMLES are of particular relevance along with special techniques based on the acoustic analogies in order to estimate the unsteady noise pressure fluctuations. Additional areas of interest of this Special Issue are physics-based and data-driven modelling, such as deep learning, applied to cases of practical relevance, not limited to the cases above mentioned. The application of such methods to optimisation as well as the propagation of uncertainties (aleatory uncertainties in flow and flight conditions and/or geometry as well as epistemic uncertainties, e.g., concerned with turbulence modelling) onto quantities of interest related to performance and noise are also very appreciated. 

Prof. Dr. Andrea Da-Ronch
Prof. Dr. Marcello Righi
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.


  • multi-physics
  • high-fidelity
  • aerospace
  • uncertainty quantification
  • turbulence modelling
  • deep learning

Published Papers (1 paper)

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19 pages, 6114 KiB  
Estimation and Separation of Longitudinal Dynamic Stability Derivatives with Forced Oscillation Method Using Computational Fluid Dynamics
Aerospace 2021, 8(11), 354; https://doi.org/10.3390/aerospace8110354 - 19 Nov 2021
Cited by 3 | Viewed by 3320
This paper focuses on estimating dynamic stability derivatives using a computational fluid dynamics (CFD)-based force oscillation method, and on separating the coupled dynamic derivatives terms obtained from the method. A transient RANS solver is used to calculate the time history of aerodynamic moments [...] Read more.
This paper focuses on estimating dynamic stability derivatives using a computational fluid dynamics (CFD)-based force oscillation method, and on separating the coupled dynamic derivatives terms obtained from the method. A transient RANS solver is used to calculate the time history of aerodynamic moments for a test model oscillating about the center of gravity, from which the coupled dynamic derivatives are estimated. The separation of the coupled derivatives term is carried out by simulating simple harmonic oscillation motions such as plunging motion and flapping motion which can isolate the pitching moment due to AOA rate (Cmα˙) and the pitching moment due to pitch rate (Cmq), respectively. The periodic motions are implemented using a CFD dynamic mesh technique with user-defined function (UDF). For the validation test, steady and unsteady simulations are performed on the Army-Navy Finner Missile model. The static aerodynamic moments and pressure distribution, as well as the coupled dynamic derivative results from the pitching oscillation mode, show good agreement with the previously published wind tunnel tests and CFD analysis data. In order to separate the coupled derivative terms, two additional harmonic oscillation modes of plunging and flapping motions are tested with the angle of attack variations from 0 to 85 degrees at a supersonic speed to provide real insight on the missile maneuverability. The cross-validation study between the three oscillation modes indicates the summation of the individual plunging and flapping results becoming nearly identical to the coupled derivative results from the pitching motion, which implies the entire set of coupled and separated dynamic derivative terms can be effectively estimated with only two out of three modes. The advantages and disadvantages of each method are discussed to determine the efficient approach of estimating the dynamic stability derivatives using the forced oscillation method. Full article
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