Pub Date : 2026-02-08DOI: 10.1016/j.ast.2026.111877
Yijing An , Huajie Xiong , Zengpei Liu , Yuxuan Gao , Zhihong Zhou
Timing control of electro-thermal anti-icing systems for aircraft and aero-engines often rely on empirical methods, leading to excessive energy consumption or insufficient heating that compromises flight safety. This study identifies stagnation point temperature as the key parameter for analysis and investigates the effects of environmental temperature, velocity, liquid water content (LWC), and medium volume diameter (MVD) on anti-icing performance. Quantitative relationships between these parameters and the timing control of anti-icing are derived. Additionally, the study explores the coupled effects of these parameters, introducing the icing influence factor , as a novel metric. A multiphysics-coupled simulation method was developed through secondary development in CFD, integrating airflow, droplet impingement, and transient heat conduction models. The accuracy of this numerical approach was validated by comparison with icing wind tunnel experiments. A mathematical model linking this factor to the timing control process is established, offering valuable insights that can inform design and optimization of electro-thermal anti-icing systems.
{"title":"Effects of icing and flight factors on surface temperature and heating time on composite electrothermal protection system","authors":"Yijing An , Huajie Xiong , Zengpei Liu , Yuxuan Gao , Zhihong Zhou","doi":"10.1016/j.ast.2026.111877","DOIUrl":"10.1016/j.ast.2026.111877","url":null,"abstract":"<div><div>Timing control of electro-thermal anti-icing systems for aircraft and aero-engines often rely on empirical methods, leading to excessive energy consumption or insufficient heating that compromises flight safety. This study identifies stagnation point temperature as the key parameter for analysis and investigates the effects of environmental temperature, velocity, liquid water content (LWC), and medium volume diameter (MVD) on anti-icing performance. Quantitative relationships between these parameters and the timing control of anti-icing are derived. Additionally, the study explores the coupled effects of these parameters, introducing the icing influence factor <span><math><msub><mi>α</mi><mi>E</mi></msub></math></span>, as a novel metric. A multiphysics-coupled simulation method was developed through secondary development in CFD, integrating airflow, droplet impingement, and transient heat conduction models. The accuracy of this numerical approach was validated by comparison with icing wind tunnel experiments. A mathematical model linking this factor to the timing control process is established, offering valuable insights that can inform design and optimization of electro-thermal anti-icing systems.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"174 ","pages":"Article 111877"},"PeriodicalIF":5.8,"publicationDate":"2026-02-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146138313","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2026-02-08DOI: 10.1016/j.ast.2026.111878
Yaping Hu , Weiliang Zheng , Chen Wu , Yuxin Fan , Yaxin Du , Haoyu Yuan , Tianyi Zhang , Shuliang Jing
The impingement-film composite anti-icing provides higher heating efficiency and significant application potential for aircraft compared to conventional hot-air anti-icing. While prior studies have focused on stationary components, this study investigates the anti-icing performance of a full-scale rotating spinner via a combined experimental and numerical approach at high rotational speeds. Surface temperature was measured using a calibrated infrared thermal imager, while water film flow and ice evolution were captured with a high-speed camera. The numerical model couples external and internal airflow, heat transfer, surface water film dynamics with phase change, and solid conduction. Results indicate that the surface temperature initially rises slightly and then decreases, peaking near the fourth row of film holes. Predicted surface temperatures agree well with the experimental data within the uncertainty bands, yielding a mean absolute error of 1.5°C. The composite anti-icing mechanism is attributed to the combined effects of internal hot-air impingement heating and an external protective film formed by the ejected hot air, which simultaneously heats the surface and suppresses droplet impingement. Under the studied conditions, the rotating spinner remains fully protected at freestream temperatures slightly above −10°C. At −20°C, a continuous annular runback ice layer forms downstream of the film-hole region, with a maximum thickness of approximately 15 mm. In contrast, a stationary spinner under identical conditions exhibits an average surface temperature about 2.3°C lower, a larger ice accretion area, and a maximum ice thickness of 20 mm.
{"title":"Investigation of impingement-film composite anti-icing on a rotating spinner","authors":"Yaping Hu , Weiliang Zheng , Chen Wu , Yuxin Fan , Yaxin Du , Haoyu Yuan , Tianyi Zhang , Shuliang Jing","doi":"10.1016/j.ast.2026.111878","DOIUrl":"10.1016/j.ast.2026.111878","url":null,"abstract":"<div><div>The impingement-film composite anti-icing provides higher heating efficiency and significant application potential for aircraft compared to conventional hot-air anti-icing. While prior studies have focused on stationary components, this study investigates the anti-icing performance of a full-scale rotating spinner via a combined experimental and numerical approach at high rotational speeds. Surface temperature was measured using a calibrated infrared thermal imager, while water film flow and ice evolution were captured with a high-speed camera. The numerical model couples external and internal airflow, heat transfer, surface water film dynamics with phase change, and solid conduction. Results indicate that the surface temperature initially rises slightly and then decreases, peaking near the fourth row of film holes. Predicted surface temperatures agree well with the experimental data within the uncertainty bands, yielding a mean absolute error of 1.5°C. The composite anti-icing mechanism is attributed to the combined effects of internal hot-air impingement heating and an external protective film formed by the ejected hot air, which simultaneously heats the surface and suppresses droplet impingement. Under the studied conditions, the rotating spinner remains fully protected at freestream temperatures slightly above −10°C. At −20°C, a continuous annular runback ice layer forms downstream of the film-hole region, with a maximum thickness of approximately 15 mm. In contrast, a stationary spinner under identical conditions exhibits an average surface temperature about 2.3°C lower, a larger ice accretion area, and a maximum ice thickness of 20 mm.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"174 ","pages":"Article 111878"},"PeriodicalIF":5.8,"publicationDate":"2026-02-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146146830","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2026-02-07DOI: 10.1016/j.ast.2026.111867
X.F. Chen , W. Zhang , Y.F. Zhang
This study is the first to investigate the complex nonlinear dynamics of the blisk structure under both parametric, external and extreme random excitations. The extreme load is modeled by Lévy colored noise with heavy-tailed characteristics and temporal correlation. The amplitude-frequency response equations are derived using the averaging method. The amplitude-frequency response curves reveal the hardening nonlinearity and bistable characteristics of the blisk system under primary parametric resonance and 1:1 internal resonance. Notably, a low-frequency side peak in the response of the disk signifies energy transfer from the blade to the disk. Within the bistable region, Lévy colored noise induces the occurrence of stochastic switching between low- and high-amplitude oscillation states, as well as stochastic resonance. Importantly, larger noise intensities or shorter correlation times lead to persistent high-amplitude oscillations, which are observable through the time history and wavelet transform. This phenomenon may result in fatigue damage to the blisk structure and even exert a catastrophic impact on aircraft safety. Therefore, we introduce the mean first passage time and define a transition probability to quantify this state transition. The results demonstrate that greater noise intensity, shorter correlation time, or a smaller stability index markedly increase the likelihood of the catastrophic transition. The above findings can provide new theoretical support for the long-term stable operation, structural health monitoring, and fault diagnosis of aeroengines in extreme environments.
{"title":"Maintaining long-term stability of aeroengines under extreme environments: insights from a stochastic blisk model subjected to Lévy colored noise","authors":"X.F. Chen , W. Zhang , Y.F. Zhang","doi":"10.1016/j.ast.2026.111867","DOIUrl":"10.1016/j.ast.2026.111867","url":null,"abstract":"<div><div>This study is the first to investigate the complex nonlinear dynamics of the blisk structure under both parametric, external and extreme random excitations. The extreme load is modeled by Lévy colored noise with heavy-tailed characteristics and temporal correlation. The amplitude-frequency response equations are derived using the averaging method. The amplitude-frequency response curves reveal the hardening nonlinearity and bistable characteristics of the blisk system under primary parametric resonance and 1:1 internal resonance. Notably, a low-frequency side peak in the response of the disk signifies energy transfer from the blade to the disk. Within the bistable region, Lévy colored noise induces the occurrence of stochastic switching between low- and high-amplitude oscillation states, as well as stochastic resonance. Importantly, larger noise intensities or shorter correlation times lead to persistent high-amplitude oscillations, which are observable through the time history and wavelet transform. This phenomenon may result in fatigue damage to the blisk structure and even exert a catastrophic impact on aircraft safety. Therefore, we introduce the mean first passage time and define a transition probability to quantify this state transition. The results demonstrate that greater noise intensity, shorter correlation time, or a smaller stability index markedly increase the likelihood of the catastrophic transition. The above findings can provide new theoretical support for the long-term stable operation, structural health monitoring, and fault diagnosis of aeroengines in extreme environments.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"174 ","pages":"Article 111867"},"PeriodicalIF":5.8,"publicationDate":"2026-02-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146135213","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2026-02-07DOI: 10.1016/j.ast.2026.111858
V. Rolland , B. Shoesmith , E. Timofeev
This paper modifies the semi-analytical model (the MOCMR model) of Mach reflection in axisymmetric wedge-generated supersonic flow by Shoesmith and Timofeev (Shock Waves 31, 945-957 (2021)) to predict Mach reflection configurations at the axis of symmetry in an overexpanded jet just downstream from the exit of a nozzle. The jet flow is considered to be a steady, inviscid flow of an ideal gas with constant specific heats. Similar to the original MOCMR model, the MOCMR model for jet flow is based on a number of flowfields solved using the method of characteristics, a Mach stream flowfield solved by quasi-one-dimensional relations, and the three-shock theory at the triple point. The modifications include the incorporation of the jet boundary instead of a wedge surface, the addition of the Prandtl-Meyer expansion fan resulting from the interaction of the reflected shock with the jet boundary, and the method to efficiently and accurately resolve very small Mach disks. The results for flowfield structure and Mach disk radius and location are extensively compared with the experimental and numerical ones available in the literature as well as with the inviscid numerical simulations using an in-house adaptive unstructured finite-volume flow solver. The influence of various model assumptions on accuracy is examined. The proposed model is demonstrated to produce results of similar accuracy using considerably less computational resources as compared to time-marching CFD simulations, at the same time directly providing quantities which are difficult to extract from CFD flowfields. The application of the developed model lends additional support to the conjecture that seemingly regular reflections observed at the axis of symmetry in some physical experiments are due to insufficient optical resolution to discern a very small Mach disk. Furthermore, parametric studies are conducted for a range of exit Mach numbers and nozzle pressure ratios and the influence of these parameters on Mach disk radius and the slip line is examined.
{"title":"A model of Mach reflection in axisymmetric steady overexpanded jets: Development and applications","authors":"V. Rolland , B. Shoesmith , E. Timofeev","doi":"10.1016/j.ast.2026.111858","DOIUrl":"10.1016/j.ast.2026.111858","url":null,"abstract":"<div><div>This paper modifies the semi-analytical model (the MOCMR model) of Mach reflection in axisymmetric wedge-generated supersonic flow by Shoesmith and Timofeev (Shock Waves 31, 945-957 (2021)) to predict Mach reflection configurations at the axis of symmetry in an overexpanded jet just downstream from the exit of a nozzle. The jet flow is considered to be a steady, inviscid flow of an ideal gas with constant specific heats. Similar to the original MOCMR model, the MOCMR model for jet flow is based on a number of flowfields solved using the method of characteristics, a Mach stream flowfield solved by quasi-one-dimensional relations, and the three-shock theory at the triple point. The modifications include the incorporation of the jet boundary instead of a wedge surface, the addition of the Prandtl-Meyer expansion fan resulting from the interaction of the reflected shock with the jet boundary, and the method to efficiently and accurately resolve very small Mach disks. The results for flowfield structure and Mach disk radius and location are extensively compared with the experimental and numerical ones available in the literature as well as with the inviscid numerical simulations using an in-house adaptive unstructured finite-volume flow solver. The influence of various model assumptions on accuracy is examined. The proposed model is demonstrated to produce results of similar accuracy using considerably less computational resources as compared to time-marching CFD simulations, at the same time directly providing quantities which are difficult to extract from CFD flowfields. The application of the developed model lends additional support to the conjecture that seemingly regular reflections observed at the axis of symmetry in some physical experiments are due to insufficient optical resolution to discern a very small Mach disk. Furthermore, parametric studies are conducted for a range of exit Mach numbers and nozzle pressure ratios and the influence of these parameters on Mach disk radius and the slip line is examined.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"174 ","pages":"Article 111858"},"PeriodicalIF":5.8,"publicationDate":"2026-02-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146135212","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2026-02-07DOI: 10.1016/j.ast.2026.111871
Antonio Gregorio, Fabrizio Borgna, Roberta Fusaro, Giuseppe Narducci, Nicole Viola
{"title":"Eco-design vision for reusable vertical launch vehicles supported by multi-disciplinary design methodology and framework","authors":"Antonio Gregorio, Fabrizio Borgna, Roberta Fusaro, Giuseppe Narducci, Nicole Viola","doi":"10.1016/j.ast.2026.111871","DOIUrl":"https://doi.org/10.1016/j.ast.2026.111871","url":null,"abstract":"","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"92 1","pages":""},"PeriodicalIF":5.6,"publicationDate":"2026-02-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146135214","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2026-02-06DOI: 10.1016/j.ast.2026.111866
Samandar Khan Afridi , Shakoor Akhtar , Talha Zafar Khan , Mohsin Ali Koondhar , Ibrahim Mahariq , Ezzeddine Touti
This paper investigates the feasibility and effectiveness of a Parachute Recovery System (PRS) as an advanced airframe safety enhancement for commercial aircraft, focusing on the Boeing 777. A mixed-methods approach integrates analytical, order-of-magnitude aerodynamic modeling, expert qualitative assessments, and real-world case studies. Simulation results indicate a generated drag force of approximately 26.4 kN, demonstrating the PRS capability to achieve limited drag contribution under idealized descent assumptions during in-flight emergencies. Evidence from Cirrus SR20 and SR22 aircraft further validates PRS performance, achieving safe, low-impact landings with high survivability rates. However, large-scale implementation poses considerable engineering, financial, and regulatory challenges, including structural reinforcement, deployment reliability, and certification complexity. The cost-benefit analysis suggests that although initial and maintenance costs are significant, they may be offset by long-term safety improvements and reduced insurance liabilities. The study recommends the integration of lightweight composite materials, multi-stage deployment systems, comprehensive testing, and specialized pilot training, alongside collaboration among manufacturers, airlines, and regulatory authorities to streamline certification and operational adoption. The findings highlight the potential of PRS to advance next-generation aviation safety, enhance passenger survivability, and establish new benchmarks in commercial aircraft design and emergency recovery systems.
{"title":"Exploring the feasibility of parachute recovery systems for catastrophic failures in passenger aircraft","authors":"Samandar Khan Afridi , Shakoor Akhtar , Talha Zafar Khan , Mohsin Ali Koondhar , Ibrahim Mahariq , Ezzeddine Touti","doi":"10.1016/j.ast.2026.111866","DOIUrl":"10.1016/j.ast.2026.111866","url":null,"abstract":"<div><div>This paper investigates the feasibility and effectiveness of a Parachute Recovery System (PRS) as an advanced airframe safety enhancement for commercial aircraft, focusing on the Boeing 777. A mixed-methods approach integrates analytical, order-of-magnitude aerodynamic modeling, expert qualitative assessments, and real-world case studies. Simulation results indicate a generated drag force of approximately 26.4 kN, demonstrating the PRS capability to achieve limited drag contribution under idealized descent assumptions during in-flight emergencies. Evidence from Cirrus SR20 and SR22 aircraft further validates PRS performance, achieving safe, low-impact landings with high survivability rates. However, large-scale implementation poses considerable engineering, financial, and regulatory challenges, including structural reinforcement, deployment reliability, and certification complexity. The cost-benefit analysis suggests that although initial and maintenance costs are significant, they may be offset by long-term safety improvements and reduced insurance liabilities. The study recommends the integration of lightweight composite materials, multi-stage deployment systems, comprehensive testing, and specialized pilot training, alongside collaboration among manufacturers, airlines, and regulatory authorities to streamline certification and operational adoption. The findings highlight the potential of PRS to advance next-generation aviation safety, enhance passenger survivability, and establish new benchmarks in commercial aircraft design and emergency recovery systems.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"173 ","pages":"Article 111866"},"PeriodicalIF":5.8,"publicationDate":"2026-02-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146134792","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2026-02-06DOI: 10.1016/j.ast.2026.111852
Jiliang Xie, Kemao Ma
A nonzero-sum Target-Attacker-Defender game is investigated, where the target attempts to evade the attacker, the attacker aims to capture the target while evading the defenders, and the multiple defenders strive to capture the attacker while achieving the cooperation among them. A new class of cost functions segmented by the game times are developed to reflect the objectives of the respective agents. By optimizing these cost functions, the optimal strategies of the agents are derived, forming an equilibrium solution of the differential game. Furthermore, considering the communication interactions between the defenders, distributed defending strategies are derived for the defenders, where each defender’s strategy depends only on its own information and that of its connected neighbors. It is proved that the distributed strategies of the defenders, together with the optimal strategies of the target and the attacker, form an ϵ equilibrium solution of the differential game. The designed strategies are applied to a terminal guidance scenario, where a tactical missile intercepts an actively-defended target. Simulations are conducted to verify the effectiveness of the design.
{"title":"Distributed defending strategies in target-attacker-defender game with applications to cooperative guidance","authors":"Jiliang Xie, Kemao Ma","doi":"10.1016/j.ast.2026.111852","DOIUrl":"10.1016/j.ast.2026.111852","url":null,"abstract":"<div><div>A nonzero-sum Target-Attacker-Defender game is investigated, where the target attempts to evade the attacker, the attacker aims to capture the target while evading the defenders, and the multiple defenders strive to capture the attacker while achieving the cooperation among them. A new class of cost functions segmented by the game times are developed to reflect the objectives of the respective agents. By optimizing these cost functions, the optimal strategies of the agents are derived, forming an equilibrium solution of the differential game. Furthermore, considering the communication interactions between the defenders, distributed defending strategies are derived for the defenders, where each defender’s strategy depends only on its own information and that of its connected neighbors. It is proved that the distributed strategies of the defenders, together with the optimal strategies of the target and the attacker, form an ϵ equilibrium solution of the differential game. The designed strategies are applied to a terminal guidance scenario, where a tactical missile intercepts an actively-defended target. Simulations are conducted to verify the effectiveness of the design.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"173 ","pages":"Article 111852"},"PeriodicalIF":5.8,"publicationDate":"2026-02-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146134793","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2026-02-06DOI: 10.1016/j.ast.2026.111773
Kapil Aryal , Vivek Nair , Nishith K R Gorla , Sandeep Patil , Brian H. Dennis
This paper compares two non-intrusive reduced-order models for predicting surface-pressure fields in inverse airfoil shape identification with deforming meshes. Proper Orthogonal Decomposition (POD) and feed-forward neural networks map geometric and flow parameters to POD coefficients for rapid field reconstruction. The models are trained on 200 CFD snapshots of steady two-dimensional laminar separated flow () using either coarse or fine meshes to quantify accuracy-cost trade-offs. Results show that the coarse-mesh model achieves accuracy similar to the fine-mesh model while reducing offline training cost by nearly sixfold. Both models exhibit similar robustness in inverse design under noisy targets, and the reduced-order formulation smooths discretization-induced noise in the objective function, improving optimizer convergence.
{"title":"Inverse airfoil shape identification using POD-ANN ROMs: A coarse Mesh approach for computational efficiency","authors":"Kapil Aryal , Vivek Nair , Nishith K R Gorla , Sandeep Patil , Brian H. Dennis","doi":"10.1016/j.ast.2026.111773","DOIUrl":"10.1016/j.ast.2026.111773","url":null,"abstract":"<div><div>This paper compares two non-intrusive reduced-order models for predicting surface-pressure fields in inverse airfoil shape identification with deforming meshes. Proper Orthogonal Decomposition (POD) and feed-forward neural networks map geometric and flow parameters to POD coefficients for rapid field reconstruction. The models are trained on 200 CFD snapshots of steady two-dimensional laminar separated flow (<span><math><mrow><mi>R</mi><mi>e</mi><mo>=</mo><mn>1000</mn></mrow></math></span>) using either coarse or fine meshes to quantify accuracy-cost trade-offs. Results show that the coarse-mesh model achieves accuracy similar to the fine-mesh model while reducing offline training cost by nearly sixfold. Both models exhibit similar robustness in inverse design under noisy targets, and the reduced-order formulation smooths discretization-induced noise in the objective function, improving optimizer convergence.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"174 ","pages":"Article 111773"},"PeriodicalIF":5.8,"publicationDate":"2026-02-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146134790","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2026-02-05DOI: 10.1016/j.ast.2026.111857
Xintao Zhang , Gang Sun , Lijuan Feng , Yongfeng Jin , Anran Ju
With the increasing diameter of high-bypass-ratio turbofan nacelles, reducing nacelle weight has become a critical design objective. Shortening the inlet length is an effective approach to achieve this goal but poses challenges under crosswind conditions due to flow separation and distortion risks. This study investigates the aerodynamic characteristics and optimization of short inlets subjected to crosswind. A distortion mechanism is revealed, showing that the coupling between the unsteady ground vortex and the diffuser flow is the key cause of flow instability and pressure distortion. Based on steady-state computational fluid dynamics analysis, a wall-velocity-based criterion is proposed for rapid engineering assessment of separation. A decoupled intuitive class shape transformation (DiCST) parameterization method is developed to independently control the fore-body and aft-body of the inlet, enhancing local shaping flexibility. Furthermore, a multi-objective optimization framework combining support vector machines with a genetic algorithm is established, transforming distortion evaluation into a flow-separation classification problem. The optimized short inlet achieves a length reduction of approximately 0.05 times the engine diameter in average while maintaining distortion within acceptable limits. Wind tunnel tests confirm that the optimized configuration suppresses flow separation effectively under crosswind conditions, validating the proposed design methodology.
{"title":"Aerodynamic optimization strategy and experimental study on short inlet in crosswind conditions using decoupled intuitive class shape transformation curves","authors":"Xintao Zhang , Gang Sun , Lijuan Feng , Yongfeng Jin , Anran Ju","doi":"10.1016/j.ast.2026.111857","DOIUrl":"10.1016/j.ast.2026.111857","url":null,"abstract":"<div><div>With the increasing diameter of high-bypass-ratio turbofan nacelles, reducing nacelle weight has become a critical design objective. Shortening the inlet length is an effective approach to achieve this goal but poses challenges under crosswind conditions due to flow separation and distortion risks. This study investigates the aerodynamic characteristics and optimization of short inlets subjected to crosswind. A distortion mechanism is revealed, showing that the coupling between the unsteady ground vortex and the diffuser flow is the key cause of flow instability and pressure distortion. Based on steady-state computational fluid dynamics analysis, a wall-velocity-based criterion is proposed for rapid engineering assessment of separation. A decoupled intuitive class shape transformation (DiCST) parameterization method is developed to independently control the fore-body and aft-body of the inlet, enhancing local shaping flexibility. Furthermore, a multi-objective optimization framework combining support vector machines with a genetic algorithm is established, transforming distortion evaluation into a flow-separation classification problem. The optimized short inlet achieves a length reduction of approximately 0.05 times the engine diameter in average while maintaining distortion within acceptable limits. Wind tunnel tests confirm that the optimized configuration suppresses flow separation effectively under crosswind conditions, validating the proposed design methodology.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"174 ","pages":"Article 111857"},"PeriodicalIF":5.8,"publicationDate":"2026-02-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146134794","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
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