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Aerospace
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Selected Papers from 10th International Conference on Vortex Flow Mechanics
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Selected Papers from 10th International Conference on Vortex Flow Mechanics

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

Deadline for manuscript submissions: closed (15 April 2024) | Viewed by 5537

Special Issue Editors

Prof. Dr. Xiande Fang

E-Mail Website
Guest Editor
College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, 29 Yudao St., Nanjing 210016, China
Interests: aircraft environmental control; avionics cooling; thermal control; aircraft air conditioning; boiling heat transfer; condensing heat transfer; flow resistance
Prof. Dr. Nikolai Kornev

E-Mail Website
Guest Editor
Chair of Modelling and Simulation, University of Rostock, Albert-Einstein-Str. 2, 18059 Rostock, Germany
Interests: numerical thermodynamics and fluid mechanics; heat and masstransfer; mixture; turbulencetheory
Prof. Dr. Zhifu Zhou

E-Mail Website
Guest Editor
State Key Laboratory of Multiphase Flow in Power Engineering, Xi’an Jiaotong University, Xi’an 710049, China
Interests: flashing spray and dynamic spray cooling; internal flow of nozzles and micro-tubes; spray simulation and droplet evaporation; thermal loads of hypersonic vehicles
Prof. Dr. Yevhenii Shkvar

E-Mail Website
Guest Editor
1. College of Engineering, Zhejiang Normal University, Jinhua 321001, China
2. Institute of Hydromechanics, National Academy of Sciences of Ukraine, Kyiv 03680, Ukraine
Interests: airfoil flow control; turbulent boundary layer

Special Issue Information

Dear Colleagues,

The 10th International Conference on Vortex Flow Mechanics (ICVFM 2023) will be held on 16–19 October 2023 at Nanjing University of Aeronautics and Astronautics, Nanjing, China. The conference will be held onsite and online.

ICVFM 2023 is the tenth conference in a series of successful meetings commenced in Kobe in 1999 and continued in Istanbul (2001), Yokohama (2005), Daejeon (2008), San Leucio (2010), Nagoya (2014), Rostock (2016), Xi’an (2018), and Patras (2021). The purpose of ICVFM 2023 is to provide a communication platform for international researchers, engineers, and practitioners in the field of vortex physics, vortex modeling, and other fluid applications.

Aerospace is cooperating with ICVFM 2023. Authors of outstanding papers related to aerospace presented at the conference are invited to submit extended versions of their work to this Special Issue for publication. We are seeking manuscripts that report new research in the field of aerospace on, but not limited to, the following:

  • Turbulent flow;
  • Multiphase flow;
  • Reacting flow;
  • Free-shear flow;
  • Stratified flow;
  • Bio-inspired fluid mechanics;
  • Computation fluid mechanics;
  • Flow measurements;
  • Flow control;
  • Turbomachinery;
  • Aeroacoustics;
  • Aerodynamic design optimization;
  • Flow-induced vibration;
  • Scientific visualization methods;
  • Vortex dynamics.

Prof. Dr. Xiande Fang
Prof. Dr. Nikolai Kornev
Prof. Dr. Zhifu Zhou
Prof. Dr. Yevhenii Shkvar
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.

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Further information on MDPI's Special Issue polices can be found here.

Published Papers (4 papers)

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Research

24 pages, 3323 KiB  
Article
New Data-Driven Models of Mass Flow Rate and Isentropic Efficiency of Dynamic Compressors
by Xiande Fang, Yuxiang Fang, Yang Yang, Zhiqiang He and Bei Yang
Aerospace 2024, 11(7), 589; https://doi.org/10.3390/aerospace11070589 - 19 Jul 2024
Cited by 1 | Viewed by 1052
Abstract
Dynamic compressors are widely used in many industrial sectors, such as air, land, and marine vehicle engines, aircraft environmental control systems (ECS), air-conditioning and refrigeration, gas turbines, gas compression and injection, etc. The data-driven formulas of mass flow rate and isentropic efficiency of [...] Read more.
Dynamic compressors are widely used in many industrial sectors, such as air, land, and marine vehicle engines, aircraft environmental control systems (ECS), air-conditioning and refrigeration, gas turbines, gas compression and injection, etc. The data-driven formulas of mass flow rate and isentropic efficiency of dynamic compressors are required for the design, energy analysis, performance simulation, and control- and/or diagnosis-oriented dynamic simulation of such compressors and the related systems. This work develops data-driven models for predicting the performance of dynamic compressors, including empirical models for mass flow rate and isentropic efficiency, which have high prediction accuracy and broad application range. The performance maps of two multi-stage axial compressors of an aero engine and a centrifugal compressor of an aircraft ECS were chosen for evaluation of the existing empirical formulas and testing of the new models. There are 16 empirical models of mass flow rate and 14 empirical models of isentropic efficiency evaluated, and the results show that it is necessary to develop highly accurate empirical formulas both for mass flow rate and isentropic efficiency. With the data-driven method, two empirical models for mass flow rate and one for isentropic efficiency are developed. They are in general form, with some terms removable to make them simple while enhancing their applicability and prediction accuracy. The new models have much higher prediction accuracy than the best existing counterparts. The new mass flow rate models predict for the three compressors a mean absolute relative deviation (MAD) not greater than 1.3%, while the best existing models all have MAD > 2.0%. The new efficiency model predicts for the three compressors an MAD of 1.0%, 0.4%, and 1.9%, respectively, while the best existing model predicts for the three compressors an MAD of 1.8%, 0.8%, and 3.2%, respectively. Full article
(This article belongs to the Special Issue Selected Papers from 10th International Conference on Vortex Flow Mechanics)
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15 pages, 17595 KiB  
Article
Numerical Simulation of the Transient Thermal Load of a Sightseeing Airship Cockpit
by Xiaoyang Li, Xiaohui Lin, Changyue Xu and Zhuopei Li
Aerospace 2024, 11(2), 127; https://doi.org/10.3390/aerospace11020127 - 31 Jan 2024
Viewed by 1139
Abstract
The calculation of a cockpit’s transient thermal load is important for determining the capacity of the cockpit environmental control system, ensuring the safety of electronic equipment and increasing the health and comfort of cockpit occupants. According to the structural parameters of the cockpit [...] Read more.
The calculation of a cockpit’s transient thermal load is important for determining the capacity of the cockpit environmental control system, ensuring the safety of electronic equipment and increasing the health and comfort of cockpit occupants. According to the structural parameters of the cockpit of a sightseeing airship, a physical model is established. The turbulence model and calculation method are selected and verified. The transient thermal load within full flight envelope, the cockpit thermal loads at different times of the day, and the cockpit thermal loads under different free-flow velocities are obtained based on the Computational Fluid Dynamics (CFD) method. The cockpit transient thermal loads during different seasons are also obtained. The results show that solar radiation has a great influence on the cockpit transient thermal load. As the flight altitude increases, the thermal load decreases from 8.8 kW (H = 0 m) to 4.7 kW (H = 3000 m). With the change in the solar radiation intensity and solar radiation angle, the thermal load increases considerably, from 2.2 kW (8:00 a.m.) to 5.4 kW (12:00 a.m.). The influence of the free-flow velocity is not very obvious at an altitude of 3000 m, as discussed in this study. The influence of seasons is significant. Finally, the influence of the solar absorptivity and infrared emissivity of the cockpit surface material are studied, and the temperature distribution on the cockpit’s surface is determined. Full article
(This article belongs to the Special Issue Selected Papers from 10th International Conference on Vortex Flow Mechanics)
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14 pages, 4752 KiB  
Article
Measurement of the Convection Velocities in a Hypersonic Turbulent Boundary Layer Using Two-Point Cylindrical-Focused Laser Differential Interferometer
by Ranran Huang, Tao Xue and Jie Wu
Aerospace 2024, 11(1), 100; https://doi.org/10.3390/aerospace11010100 - 22 Jan 2024
Viewed by 1267
Abstract
A two-point cylindrical-focused laser differential interferometer (2P-CFLDI) system and a conventional Z-type Schlieren were used to measure the hypersonic turbulent boundary layer on a flat plate at Mach number Ma = 6 and Reynolds number Re = 1.08 × 106 m−1 [...] Read more.
A two-point cylindrical-focused laser differential interferometer (2P-CFLDI) system and a conventional Z-type Schlieren were used to measure the hypersonic turbulent boundary layer on a flat plate at Mach number Ma = 6 and Reynolds number Re = 1.08 × 106 m−1. The boundary layer thickness at the measurement location and the noise radiation angle were obtained by post-processing the Schlieren image. The 2P-CFLDI data underwent cross-correlation analysis to calculate the mean convective velocities at different heights and compared with previous experimental and numerical results. The experimentally measured mean convective velocities agree with the trend of available DNS and experimental results. The mean convective velocity near the wall is significantly larger than the local mean velocity and is the main noise source region. Further filtering treatment shows that the convective velocity of the disturbed structure decreases gradually with the increase in the disturbance scale. The differences between convective velocities at different scales are significantly larger outside the boundary layer than inside the boundary layer, which is in agreement with the findings of the previous hot wire experiments. Near the wall, large-scale disturbances mainly determine the localized mean convective velocity, which are the main source of noise radiation for the hypersonic turbulent boundary layer. Full article
(This article belongs to the Special Issue Selected Papers from 10th International Conference on Vortex Flow Mechanics)
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16 pages, 7773 KiB  
Article
Real Gas Effects on Receptivity to Roughness in Hypersonic Swept Blunt Flat-Plate Boundary Layers
by Yanxin Yin, Ruiyang Lu, Jianxin Liu and Zhangfeng Huang
Aerospace 2024, 11(1), 58; https://doi.org/10.3390/aerospace11010058 - 7 Jan 2024
Viewed by 1368
Abstract
Temperatures within the boundary layers of high-enthalpy hypersonic flows can soar to thousands or even tens of thousands of degrees, leading to significant real gas phenomena. Although there has been significant research on real gas effects on hypersonic boundary layer stability, their impact [...] Read more.
Temperatures within the boundary layers of high-enthalpy hypersonic flows can soar to thousands or even tens of thousands of degrees, leading to significant real gas phenomena. Although there has been significant research on real gas effects on hypersonic boundary layer stability, their impact on the boundary layer’s receptive stage is still poorly understood. Most aerodynamic boundary layers in flight vehicles are three-dimensional. Because of complex geometry and significant crossflow effects, the crossflow mode in three-dimensional boundary layers is crucial in hypersonic vehicle design. In this study, a linear stability analysis (LST) accounting for chemical nonequilibrium effects (CNE) and its adjoint form (ALST) is developed to investigate the real gas effects on the stability and receptivity of stationary crossflow modes. The results indicate that real gas effects significantly influence the receptivity of stationary crossflow modes. Specifically, chemical nonequilibrium effects destabilize the crossflow modes but reduce the receptivity coefficients of the stationary crossflow modes. The Mach number effect was also investigated. It was found that increasing the Mach number stabilizes the stationary crossflow modes, but the receptivity coefficients increase. As the Mach number progressively rises, these effects alternately dominate, leading to a non-monotonic shift in the transition position. Full article
(This article belongs to the Special Issue Selected Papers from 10th International Conference on Vortex Flow Mechanics)
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