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Aerospace
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New Results in Wind Tunnel Testing
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New Results in Wind Tunnel Testing

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

Deadline for manuscript submissions: 30 September 2025 | Viewed by 1632

Special Issue Editor

Prof. Dr. Bosko Rasuo

E-Mail Website
Guest Editor
Faculty of Mechanical Engineering, University of Belgrade, Belgrade, Serbia
Interests: computational and experimental aerodynamics; wind tunnel technology; flow control; flight mechanics and aircraft performance; aeroacoustics; aeroelasticity; composite materials/structures and fatigue; failure analysis; crashworthiness; fluid–structure interaction; experimental fracture mechanics; fatigue of aircraft materials and structures; bio-inspired aerodynamical and structural design; UAVs; artificial intelligence; wind energy

Special Issue Information

Dear Colleagues,

To successfully design the aerodynamics of new modern aircraft, it is necessary to know the accurate aerodynamic characteristics of the whole aircraft as well as of its individual constituent parts. Since there is still no completely accurate mathematical model of turbulent flows, we cannot completely solve the aerodynamic design problem by computer simulation and calculation only. We still have to solve many problems related to aerodynamic design by performing tests in wind tunnels. However, wind tunnel simulation is connected with many problems that cause distortions in the flow conditions around the tested models, which ultimately results in the inaccuracy of the measured aerodynamic values. There are many reasons for this, but it is quite understandable that even the best wind tunnels cannot provide conditions that accurately simulate flows around the model that are identical to the flows in the free air. Therefore, resolving the problem related to the definition and elimination of wind tunnel wall interference is a continuing task requiring experimental and theoretical research, either during the construction of new wind tunnels or during their use.

However, the fact is that wind tunnels are increasingly used today to calibrate CFD simulation codes and less and less to directly design new aircraft in order to reduce very expensive wind tunnel experiments. In the last three years, the role of wind tunnels in the field of aerospace has expanded even more, especially in the era of accelerated development and application of artificial intelligence and implementation of machine learning in aerodynamics and solving complex problems of aeroelasticity of sophisticated aircraft structures.

The focus of this special issue, called "New Results in Wind Tunnel Testing", will be the research and development of modern aircraft by testing in subsonic, transonic, supersonic, and hypersonic wind tunnels, covering a velocity range from 0.2 to 15 Mach.

Prof. Dr. Bosko Rasuo
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

  • subsonic/transonic/supersonic/hypersonic wind tunnel
  • measurement techniques
  • measurement systems
  • test methodology
  • innovative approaches

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Published Papers (2 papers)

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Research

21 pages, 1303 KiB  
Article
A Multi-Mode Dynamic Fusion Mach Number Prediction Framework
by Luping Zhao, Weihao Li and Wentao Xu
Aerospace 2025, 12(7), 569; https://doi.org/10.3390/aerospace12070569 - 23 Jun 2025
Viewed by 209
Abstract
The precise control of Mach numbers in supersonic and hypersonic compressor wind tunnel systems is a critical challenge in aerodynamic research. Although existing studies have improved prediction accuracy to some extent through machine learning methods, they generally neglect the multi-mode characteristics of complex [...] Read more.
The precise control of Mach numbers in supersonic and hypersonic compressor wind tunnel systems is a critical challenge in aerodynamic research. Although existing studies have improved prediction accuracy to some extent through machine learning methods, they generally neglect the multi-mode characteristics of complex wind tunnel systems, limiting the generalizability of the models. To address this issue, the present study proposes a multi-mode dynamic fusion Mach number prediction framework that integrates strategies of segmented modeling and cross-modal information fusion. First, single-mode segmented prediction models are constructed on the basis of Multi-output Support Vector Regression (MSVR), with hyperparameters optimized to capture the characteristics of individual modes. Second, the Partial Least Squares (PLS) method is employed to explore the correlations between historical and new modes, dynamically selecting the optimal prediction model and updating the historical mode repository. Experimental results demonstrate that the multi-mode dynamic fusion framework reduces the Root Mean Square Error (RMSE) by 70.57%, 56.4%, and 63.64% compared to Support Vector Regression (SVR), PLS, and Long Short-term Memory (LSTM) networks across six operating conditions. The framework proposed in this paper enhances Mach number prediction accuracy while improving model generalizability. Full article
(This article belongs to the Special Issue New Results in Wind Tunnel Testing)
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15 pages, 7479 KiB  
Article
New Transonic Tests of HB-2 Hypersonic Standard Models in the VTI T-38 Trisonic Wind Tunnel
by Dijana Damljanović, Đorđe Vuković, Goran Ocokoljić and Boško Rašuo
Aerospace 2025, 12(2), 131; https://doi.org/10.3390/aerospace12020131 - 9 Feb 2025
Cited by 1 | Viewed by 1003
Abstract
Recent experience has shown that test results of standard wind tunnel models under off-design conditions could be a useful aid in preparations of some nonstandard wind tunnel tests. However, reference data for such conditions do not exist, or they are scarce. Therefore, off-design [...] Read more.
Recent experience has shown that test results of standard wind tunnel models under off-design conditions could be a useful aid in preparations of some nonstandard wind tunnel tests. However, reference data for such conditions do not exist, or they are scarce. Therefore, off-design transonic wind tunnel tests of the HB-2 standard models were executed in the VTI T-38 wind tunnel as a supplement to the supersonic tests of the same models under design-intent conditions, for which reference results were available. New tests were conducted so that test envelopes partially overlapped with those from available supersonic reference data. Good agreements of results with references were confirmed in the overlapped ranges, so it was assumed that, by implication, the obtained results were also valid in the transonic range of conditions, with an observation that the effects of sting diameter were much more pronounced in the transonic range than in the supersonic one. HB-2 models were tested in two sizes, using two different wind tunnel balances for each model, so that the results can be used with more confidence. Full article
(This article belongs to the Special Issue New Results in Wind Tunnel Testing)
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