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Aerospace
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Recent Advances in Applied Aerodynamics
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Recent Advances in Applied Aerodynamics

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

Deadline for manuscript submissions: 28 February 2025 | Viewed by 8593

Special Issue Editor

Prof. Dr. Cheolheui Han

E-Mail Website
Guest Editor
Department of Aeronautical and Mechanical Design Engineering, Korea National University of Transportation, Chungju-si 27496, Republic of Korea
Interests: low speed aerodynamics; unsteady aerodynamics; formation flight; wing-in-ground effect aircraft design; biomimetics

Special Issue Information

Dear Colleagues,

Applied aerodynamics seeks to understand and utilize the fundamental aspects of fluid flow in the analysis, design, and integration of aerodynamic geometries. This field covers a broad range of applications, generally involving any object that experiences aerodynamic forces in fluid flow, though common applications include fixed-wing or rotary-wing aircraft, wind turbines and propellers, ground and marine vehicles, internal flows, avian and insect flight, and atmospheric flows. We are seeking papers on theoretical, experimental, and computational approaches to aerodynamics applications. Areas of interest include but are not limited to: flight or ground vehicle aerodynamic design, analysis of wing/rotor/vehicle aerodynamic performance, methods for modeling aerodynamic bodies, and novel studies or technological applications related to aerodynamic applications. Specific areas of interest are listed below but work in related areas is also encouraged.

  • Aerodynamic design: analysis, methodologies, and optimization techniques;
  • Aerodynamic flow control: analytical, computational, and experimental;
  • Aerodynamic testing: ground, wind tunnel, and flight testing;
  • Aero-propulsive interactions and aerodynamics of integrated propeller systems;
  • Airfoil/wing/configuration aerodynamics;
  • Applied aeroelasticity and aerodynamic–structural dynamics interaction;
  • Applied computational fluid dynamics;
  • Boundary layer transition for aerodynamic applications;
  • CFD methods for aerodynamics applications;
  • Propeller/rotorcraft/wind turbine aerodynamics;
  • Reduced order aerodynamics modeling and system identification;
  • Transonic and supersonic aerodynamics;
  • Unsteady aerodynamics and massively separated flows.

Prof. Dr. Cheolheui Han
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

  • CFD
  • aerodynamic testing
  • design optimization
  • flow control
  • flow-structure interaction
  • boundary layer transition.

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

Published Papers (5 papers)

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Research

28 pages, 3037 KiB  
Article
Design of Input Signal for System Identification of a Generic Fighter Configuration
by Mehdi Ghoreyshi, Pooneh Aref and Jürgen Seidel
Aerospace 2024, 11(11), 883; https://doi.org/10.3390/aerospace11110883 - 26 Oct 2024
Viewed by 490
Abstract
This article investigates the design of time-accurate input signals in the angle-of-attack and pitch rate space to identify the aerodynamic characteristics of a generic triple-delta wing configuration at subsonic speeds. Regression models were created from the time history of signal simulations in DoD [...] Read more.
This article investigates the design of time-accurate input signals in the angle-of-attack and pitch rate space to identify the aerodynamic characteristics of a generic triple-delta wing configuration at subsonic speeds. Regression models were created from the time history of signal simulations in DoD HPCMP CREATETM-AV/Kestrel software. The input signals included chirp, Schroeder, pseudorandom binary sequence (PRBS), random, and sinusoidal signals. Although similar in structure, the coefficients of these regression models were estimated based on the specific input signals. The signals covered a wide range of angle-of-attack and pitch rate space, resulting in varying regression coefficients for each signal. After creating and validating the models, they were used to predict static aerodynamic data at a wide range of angles of attack but with zero pitch rate. Next, slope coefficients and dynamic derivatives in the pitch direction were estimated from each signal. These predictions were compared with each other as well as with the ONERA wind tunnel data and some CFD calculations from the DLR TAU code provided by the NATO Science and Technology Organization research task group AVT-351. Subsequently, the models were used to predict different pitch oscillations at various mean angles of attack with given amplitudes and frequencies. Again, the model predictions were compared with wind tunnel data. Final predictions involved responses to new signals from different models. A feed-forward neural network was then used to model pressure coefficients on the upper surface of the vehicle at different spanwise sections for each signal and the validated models were used to predict pressure data at different angles of attack. Overall, the models predict similar integrated forces and moments, with the main discrepancies appearing at higher angles of attack. All models failed to predict the stall behavior observed in the measurements and CFD data. Regarding the pressure data, the PRBS signal provided the best accuracy among all the models. Full article
(This article belongs to the Special Issue Recent Advances in Applied Aerodynamics)
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21 pages, 13293 KiB  
Article
Wind Tunnel Experiment and Numerical Simulation of Secondary Flow Systems on a Supersonic Wing
by Sheng Zhang, Zheng Lin, Zeming Gao, Shuai Miao, Jun Li, Lifang Zeng and Dingyi Pan
Aerospace 2024, 11(8), 618; https://doi.org/10.3390/aerospace11080618 - 28 Jul 2024
Viewed by 1312
Abstract
Aircraft secondary flow systems are small-flow circulation devices that are used for thermal and cold management, flow control, and energy generation on aircraft. The aerodynamic characteristics of main-flow-based inlets have been widely studied, but the secondary-flow-based small inlets, jets, and blowing and suction [...] Read more.
Aircraft secondary flow systems are small-flow circulation devices that are used for thermal and cold management, flow control, and energy generation on aircraft. The aerodynamic characteristics of main-flow-based inlets have been widely studied, but the secondary-flow-based small inlets, jets, and blowing and suction devices have seldom been studied. Two types of secondary flow systems embedded in a supersonic aircraft wing, a ram-air intake and a submerged intake, are researched here. Firstly, wind tunnel tests under subsonic, transonic, and supersonic conditions are carried out to test the total pressure recovery and total pressure distortion. Secondly, numerical simulations are used to analyze the flow characteristics in the secondary flow systems. The numerical results are validated with experimental data. The calculating errors of the total pressure recovery on the ram-air and submerged secondary flow systems are 8% and 10%, respectively. The simulation results demonstrate that the total pressure distortion tends to grow while the total pressure recovery drops with the increasing Mach number. As the Mach number increases from 0.4 to 2, the total pressure recovery of the ram-air secondary flow system decreases by 68% and 71% for the submerged system. Moreover, the total pressure distortion of the ram-air and submerged secondary flow systems is increased by 19.7 times and 8.3 times, respectively. Thirdly, a detailed flow mechanism is studied based on the simulation method. It is found that the flow separation at the front part of the tube is induced by adverse pressure gradients, which primarily determine the total pressure recovery at the outlet. The three-dimensional vortex in the tube is mainly caused by the change in cross-sectional shape, which influences the total pressure distortion. Full article
(This article belongs to the Special Issue Recent Advances in Applied Aerodynamics)
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18 pages, 6724 KiB  
Article
CFD Simulations and Phenomenological Modelling of Aerodynamic Stall Hysteresis of NACA 0018 Wing
by Mohamed Sereez, Nikolay Abramov and Mikhail Goman
Aerospace 2024, 11(5), 354; https://doi.org/10.3390/aerospace11050354 - 29 Apr 2024
Viewed by 1544
Abstract
Computational simulations of three-dimensional flow around a NACA 0018 wing with an aspect ratio of AR=5 were carried out by using the Unsteady Reynolds-Averaged Navier–Stokes (URANS) equations with the Shear-Stress Transport turbulence model closure. Simulations were performed to capture aerodynamic [...] Read more.
Computational simulations of three-dimensional flow around a NACA 0018 wing with an aspect ratio of AR=5 were carried out by using the Unsteady Reynolds-Averaged Navier–Stokes (URANS) equations with the Shear-Stress Transport turbulence model closure. Simulations were performed to capture aerodynamic stall hysteresis by using the developed pseudo-transient continuation (PTC) method based on a dual-time step approach in CFD OpenFOAM code. The flow was characterized by incompressible Mach number M=0.12 and moderate Reynolds number Re=0.67×106. The results obtained indicate the presence of noticeable aerodynamic hysteresis in the static dependencies of the force and moment coefficients, as well as the manifestation of bi-stable flow separation patterns, accompanied by the development of asymmetry in the stall zone. The URANS simulation results are in good agreement with the experimental data obtained for the NACA 0018 finite-aspect-ratio wing in the low-speed wind tunnel under the same test conditions. A new phenomenological bifurcation model of aerodynamic stall hysteresis under static and dynamic conditions is formulated and is proven to be able to closely match the experimental data. Full article
(This article belongs to the Special Issue Recent Advances in Applied Aerodynamics)
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29 pages, 8718 KiB  
Article
Rotor Performance Predictions for Urban Air Mobility: Single vs. Coaxial Rigid Rotors
by Jason Cornelius, Sven Schmitz, Jose Palacios, Bernadine Juliano and Richard Heisler
Aerospace 2024, 11(3), 244; https://doi.org/10.3390/aerospace11030244 - 20 Mar 2024
Cited by 1 | Viewed by 2154
Abstract
This work details the development and validation of a methodology for high-resolution rotor models used in hybrid Blade Element Momentum Theory Unsteady Reynolds Averaged Navier–Stokes (BEMT-URANS) CFD. The methodology is shown to accurately predict single and coaxial rotor performance in a fraction of [...] Read more.
This work details the development and validation of a methodology for high-resolution rotor models used in hybrid Blade Element Momentum Theory Unsteady Reynolds Averaged Navier–Stokes (BEMT-URANS) CFD. The methodology is shown to accurately predict single and coaxial rotor performance in a fraction of the time required by conventional CFD methods. The methodology has three key features: (1) a high-resolution BEMT rotor model enabling large reductions in grid size, (2) a discretized set of momentum sources to interface between the BEMT rotor model and the structured URANS flow solver, and (3) leveraging of the first two features to enable highly parallelized GPU-accelerated multirotor CFD simulations. The hybrid approach retains high-fidelity rotor inflow, wake propagation, and rotor–rotor interactional effects at a several orders of magnitude lower computational cost compared to conventional blade-resolved CFD while retaining high accuracy on steady rotor performance metrics. Rotor performance predictions of thrust and torque for both single and coaxial rotor configurations are compared to test the data that the authors obtained at the NASA Langley 14- by 22-ft. Subsonic Tunnel Facility. Simulations were run with both fully turbulent and free-transition airfoil performance tables to quantify the associated uncertainty. Single rotor thrust and torque were predicted on average within 4%. Coaxial thrust and power were predicted within an average of 5%. A vortex ring state (VRS) shielding phenomenon for coaxial rotor systems is also presented and discussed. The results support that this hybrid BEMT-URANS CFD methodology can be highly parallelized on GPU machines to obtain accurate rotor performance predictions across the full spectrum of possible UAM flight conditions in a fraction of the time required by conventional higher-fidelity methods. This strategy can be used to rapidly create look-up tables with hundreds to thousands of flight conditions using a three-dimensional multirotor CFD for UAM. Full article
(This article belongs to the Special Issue Recent Advances in Applied Aerodynamics)
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19 pages, 46914 KiB  
Article
Experimental Investigation of the Effect of Bio-Inspired Wavy Leading-Edges on Aerodynamic Performance and Flow Topologies of the Airfoil
by Hai Du, Hao Jiang, Zhangyi Yang, Haoyang Xia, Shuo Chen and Jifei Wu
Aerospace 2024, 11(3), 194; https://doi.org/10.3390/aerospace11030194 - 29 Feb 2024
Cited by 1 | Viewed by 1659
Abstract
The characteristic of delayed airfoil stalls caused by the bio-inspired Wavy Leading-Edges (WLEs) has attracted extensive attention. This paper investigated the effect of WLEs on the aerodynamic performance and flow topologies of the airfoil through wind tunnel experiments, while also discussing the flow [...] Read more.
The characteristic of delayed airfoil stalls caused by the bio-inspired Wavy Leading-Edges (WLEs) has attracted extensive attention. This paper investigated the effect of WLEs on the aerodynamic performance and flow topologies of the airfoil through wind tunnel experiments, while also discussing the flow control mechanism of WLEs. The result shows that, at small Angle of Attack (AOA), the flow through the WLEs exhibits periodic and symmetrical characteristics, where flow vortices upwash at the trough and downwash at the crest, resulting in flow from the crest to the trough. Upwash leads to the formation of a localized three-dimensional laminar separation bubble (LSB) structure at the leading edge of the trough section. At large AOA after baseline airfoil stall, the flow on the airfoil surface of WLEs presents a two-period pattern along the spanwise direction, and the separation zone and the attachment zone appear alternately, indicating that the control effect of delayed stall is accomplished by reducing the separation zone on the airfoil surface. The alternating occurrence of the separation and attachment zones is the result of intricate interactions among flows passing through multiple WLEs. This interaction causes the convergence of high-momentum attached airflows on both sides, thereby constraining the spread of the separation from the leading edge and enabling the re-attachment of separated air. The research results of this paper provide a reference for researchers to reveal the flow control mechanism of WLEs more comprehensively. Full article
(This article belongs to the Special Issue Recent Advances in Applied Aerodynamics)
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