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Energies
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Aerodynamics and Heat Transfer for Aircraft and Aerospace Systems
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Aerodynamics and Heat Transfer for Aircraft and Aerospace Systems

A special issue of Energies (ISSN 1996-1073). This special issue belongs to the section "J: Thermal Management".

Deadline for manuscript submissions: closed (20 October 2022) | Viewed by 4004

Special Issue Editors

Prof. Dr. François Morency

E-Mail Website
Guest Editor
Mechanical Engineering Department, École de Technologie Supérieure, Montréal, QC H3C1K3, Canada
Interests: Aeronautic; heat transfer; parallel calculation; atmospheric icing; computational fluid dynamics; ice protection systems; thermo fluid; surface roughness; sensitivity analysis; in-flight icing
Prof. Dr. Héloïse Beaugendre

E-Mail Website
Guest Editor
University Bordeaux, INRIA, CNRS, Bordeaux INP, IMB, UMR 5251, F-33400 Talence, France
Interests: Computational fluid dynamics; high order numerical scheme; mesh adaptation; immersed boundary method; high-performance computing; multi-physics simulations; inflight icing/deicing

Special Issue Information

Dear Colleagues, 

The predictions of aerodynamics and heat transfer are central in the design process of aircraft and aerospace systems. Although researchers have recognized the key role of aerodynamics to determine the forces acting on aircraft for several years, the limit on the net carbon emissions soon imposed by countries forces the development of more efficient aircraft. To reduce the drag, engineers study new designs taking advantage of the ever-increasing computer power and advanced 3D numerical methods. These new numerical tools need new experimental results to broaden their validity ranges, especially heat transfer measurements. Heat transfer above aerodynamic surfaces is less studied, but it plays a critical role in applications such as aircraft ice protection systems, turbine blade cooling, high-velocity flow, and hypersonic vehicles. The heat transfer prediction may become even more challenging over the rough surface that can occur during ice accretion, turbine blade wearing, or the ablation process for a re-entry vehicle. Thermal models for Reynolds-averaged Navier–Stokes solutions need improvements to increase prediction fidelity, either from a better understanding of the physical phenomenon or from additional calibration with experimental results. This Special Issue will reduce the gap between the aerodynamic and the heat transfer knowledge, by encouraging researchers to share their convective heat transfer results. 

Prof. Dr. François Morency
Prof. Dr. Héloïse Beaugendre
Guest Editors

Manuscript Submission Information

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Keywords

  • Heat transfer 
  • Turbulence modeling 
  • Wall roughness 
  • Unsteady heat transfer 
  • Convective heat transfer

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Published Papers (2 papers)

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Research

20 pages, 4536 KiB  
Article
Data-Driven Calibration of Rough Heat Transfer Prediction Using Bayesian Inversion and Genetic Algorithm
by Kevin Ignatowicz, Elie Solaï, François Morency and Héloïse Beaugendre
Energies 2022, 15(10), 3793; https://doi.org/10.3390/en15103793 - 21 May 2022
Cited by 8 | Viewed by 1976
Abstract
The prediction of heat transfers in Reynolds-Averaged Navier–Stokes (RANS) simulations requires corrections for rough surfaces. The turbulence models are adapted to cope with surface roughness impacting the near-wall behaviour compared to a smooth surface. These adjustments in the models correctly predict the skin [...] Read more.
The prediction of heat transfers in Reynolds-Averaged Navier–Stokes (RANS) simulations requires corrections for rough surfaces. The turbulence models are adapted to cope with surface roughness impacting the near-wall behaviour compared to a smooth surface. These adjustments in the models correctly predict the skin friction but create a tendency to overpredict the heat transfers compared to experiments. These overpredictions require the use of an additional thermal correction model to lower the heat transfers. Finding the correct numerical parameters to best fit the experimental results is non-trivial, since roughness patterns are often irregular. The objective of this paper is to develop a methodology to calibrate the roughness parameters for a thermal correction model for a rough curved channel test case. First, the design of the experiments allows the generation of metamodels for the prediction of the heat transfer coefficients. The polynomial chaos expansion approach is used to create the metamodels. The metamodels are then successively used with a Bayesian inversion and a genetic algorithm method to estimate the best set of roughness parameters to fit the available experimental results. Both calibrations are compared to assess their strengths and weaknesses. Starting with unknown roughness parameters, this methodology allows calibrating them and obtaining between 4.7% and 10% of average discrepancy between the calibrated RANS heat transfer prediction and the experimental results. The methodology is promising, showing the ability to finely select the roughness parameters to input in the numerical model to fit the experimental heat transfer, without an a priori knowledge of the actual roughness pattern. Full article
(This article belongs to the Special Issue Aerodynamics and Heat Transfer for Aircraft and Aerospace Systems)
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28 pages, 2437 KiB  
Article
A Galerkin Method for the Simulation of Laminar Boundary Layers on Heated Walls
by Emmanuel Radenac, Rémi Harry and Philippe Villedieu
Energies 2022, 15(9), 3267; https://doi.org/10.3390/en15093267 - 29 Apr 2022
Cited by 3 | Viewed by 1272
Abstract
This paper presents a new solution method for the calculation of laminar thermal boundary layers. The method consists of a coupling between a modal method (Galerkin method) in the direction normal to the wall and a finite volume method in the direction(s) tangential [...] Read more.
This paper presents a new solution method for the calculation of laminar thermal boundary layers. The method consists of a coupling between a modal method (Galerkin method) in the direction normal to the wall and a finite volume method in the direction(s) tangential to the wall. It is similar to an integral method in the sense that only a surface mesh is required and that the unknowns are integral quantities (corresponding to the moments up to a fixed order of the temperature profile in the direction normal to the wall). A specificity of the Galerkin method used is that the domain over which the integrals are computed has a variable size that is also an unknown of the problem. Using a series of numerical tests (representative of situations that can be encountered in aeronautics in the case of a wing equipped with a thermal ice protection system), we show that the new method allows us to predict the quantities of interest with a maximum error of a few percent, while a usual integral method (with only one unknown per mesh cell) is unable to treat the case of boundary layers on heated walls with a strong longitudinal temperature gradient, as shown in the literature. Full article
(This article belongs to the Special Issue Aerodynamics and Heat Transfer for Aircraft and Aerospace Systems)
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