Pub Date : 2026-02-10DOI: 10.1016/j.ast.2026.111894
Zhouqin Fan, Jilong Lyu, Fanfu Kong, Ruixuan Ma
{"title":"Towards Efficient Wide-Speed-Range Combustion Simulation: An ANN-FGM Model and Its Validation","authors":"Zhouqin Fan, Jilong Lyu, Fanfu Kong, Ruixuan Ma","doi":"10.1016/j.ast.2026.111894","DOIUrl":"https://doi.org/10.1016/j.ast.2026.111894","url":null,"abstract":"","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"101 1","pages":""},"PeriodicalIF":5.6,"publicationDate":"2026-02-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146153060","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}
{"title":"On the Sensitivity of Endwall Contouring of HPT Cascade to Turbulence Closure and Optimization Constraints at Design and Off-Design Conditions","authors":"Krishma Rajesh Mehta, Aditya Lakhotia, Vasudeva Tushar Nilkar, Jagdish Bagre, Nagabhushana Rao Vadlamani","doi":"10.1016/j.ast.2026.111856","DOIUrl":"https://doi.org/10.1016/j.ast.2026.111856","url":null,"abstract":"","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"9 1","pages":""},"PeriodicalIF":5.6,"publicationDate":"2026-02-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146153020","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 : 2026-02-10DOI: 10.1016/j.ast.2026.111847
Jiahui Qiu, Min Zhang, Juan Du, Mehdi Vahdati
{"title":"Effects of combined inlet pressure and temperature distortion on the internal flow of a transonic compressor","authors":"Jiahui Qiu, Min Zhang, Juan Du, Mehdi Vahdati","doi":"10.1016/j.ast.2026.111847","DOIUrl":"https://doi.org/10.1016/j.ast.2026.111847","url":null,"abstract":"","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"7 1","pages":""},"PeriodicalIF":5.6,"publicationDate":"2026-02-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146153333","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 : 2026-02-10DOI: 10.1016/j.ast.2026.111892
Z.H. Fu , W. Zhang , Y.F. Zhang
The rapid expansion of the low-altitude economy has created a growing demand for lightweight aircraft structures with high vibration resistance. To address this challenge, this study investigates the nonlinear vibrations of titanium matrix composites reinforced with twisted bilayer graphene (TBLG). A novel variable curvature shell function model, specifically designed for the complex geometries of low-altitude aircraft, to accurately capture nonlinear structural responses, is proposed to accurately capture nonlinear structural responses. Furthermore, a nonlinear functional gradient (FG-NX) distribution model of TBLG is proposed, extending beyond conventional uniform and FG-X schemes to better represent material gradation. Based on nonlinear shell theory and Rayleigh-Ritz method, the governing equations of motion are derived and solved using the harmonic balance method (HBM). The results reveal that the proposed FG-NX distribution significantly enhances structural stiffness, alters resonance characteristics, and induces complex dynamic behaviors including internal resonance, bifurcations, and chaos. These findings not only advance the fundamental understanding of nonlinear vibration in nanocomposite shells but also provide theoretical guidance for the lightweight design and vibration control of critical components in next-generation low-altitude aircraft.
{"title":"A variable curvature deep shell model for nonlinear vibrations of twisted bilayer graphene reinforced titanium composites","authors":"Z.H. Fu , W. Zhang , Y.F. Zhang","doi":"10.1016/j.ast.2026.111892","DOIUrl":"10.1016/j.ast.2026.111892","url":null,"abstract":"<div><div>The rapid expansion of the low-altitude economy has created a growing demand for lightweight aircraft structures with high vibration resistance. To address this challenge, this study investigates the nonlinear vibrations of titanium matrix composites reinforced with twisted bilayer graphene (TBLG). A novel variable curvature shell function model, specifically designed for the complex geometries of low-altitude aircraft, to accurately capture nonlinear structural responses, is proposed to accurately capture nonlinear structural responses. Furthermore, a nonlinear functional gradient (FG-NX) distribution model of TBLG is proposed, extending beyond conventional uniform and FG-X schemes to better represent material gradation. Based on nonlinear shell theory and Rayleigh-Ritz method, the governing equations of motion are derived and solved using the harmonic balance method (HBM). The results reveal that the proposed FG-NX distribution significantly enhances structural stiffness, alters resonance characteristics, and induces complex dynamic behaviors including internal resonance, bifurcations, and chaos. These findings not only advance the fundamental understanding of nonlinear vibration in nanocomposite shells but also provide theoretical guidance for the lightweight design and vibration control of critical components in next-generation low-altitude aircraft.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"174 ","pages":"Article 111892"},"PeriodicalIF":5.8,"publicationDate":"2026-02-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146153021","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}
Most previous numerical studies have focused on simplified ice shapes, whereas the present work examines more realistic discontinuous ice shapes. A modified turbulence model incorporating a separating shear-layer correction is employed to assess the flow-separation characteristics and aerodynamic performance. Infinite swept wings were first studied to eliminate root and tip effects and subsequently two distinct separation mechanisms were identified: continuous ice produces a leading-edge separation bubble with a fixed separation point, whereas discontinuous ice triggers a trailing-edge separation. Aerodynamically, discontinuous ice causes severe lift degradation due to the non-lifting nature of the trailing-edge-separation region, whereas continuous ice leads to a larger drag penalty. Further analysis of the finite-span swept-wing configurations reveals pronounced three-dimensional effects. For the continuous-ice wing, a low-pressure separation bubble near the wing root substantially enhances the lift, increasing it by 63.3 % at a 4° angle of attack relative to the infinite-span case. In contrast, for the discontinuous-ice wing, the complex spanwise flow caused by the leading-edge gap jets weaken the tip vortex. The resulting reduction in pressure difference between the upper and lower surfaces suppresses the lift enhancement, yielding only a modest 4.6 % increase in the lift coefficient compared with the infinite-span configuration.
{"title":"Flow-separation simulations of continuous and discontinuous ice on swept wings","authors":"Jiawei Chen , Ziyu Zhou , Maochao Xiao , Yufei Zhang","doi":"10.1016/j.ast.2026.111891","DOIUrl":"10.1016/j.ast.2026.111891","url":null,"abstract":"<div><div>Most previous numerical studies have focused on simplified ice shapes, whereas the present work examines more realistic discontinuous ice shapes. A modified turbulence model incorporating a separating shear-layer correction is employed to assess the flow-separation characteristics and aerodynamic performance. Infinite swept wings were first studied to eliminate root and tip effects and subsequently two distinct separation mechanisms were identified: continuous ice produces a leading-edge separation bubble with a fixed separation point, whereas discontinuous ice triggers a trailing-edge separation. Aerodynamically, discontinuous ice causes severe lift degradation due to the non-lifting nature of the trailing-edge-separation region, whereas continuous ice leads to a larger drag penalty. Further analysis of the finite-span swept-wing configurations reveals pronounced three-dimensional effects. For the continuous-ice wing, a low-pressure separation bubble near the wing root substantially enhances the lift, increasing it by 63.3 % at a 4° angle of attack relative to the infinite-span case. In contrast, for the discontinuous-ice wing, the complex spanwise flow caused by the leading-edge gap jets weaken the tip vortex. The resulting reduction in pressure difference between the upper and lower surfaces suppresses the lift enhancement, yielding only a modest 4.6 % increase in the lift coefficient compared with the infinite-span configuration.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"174 ","pages":"Article 111891"},"PeriodicalIF":5.8,"publicationDate":"2026-02-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146153019","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 : 2026-02-10DOI: 10.1016/j.ast.2026.111803
Sai Gowtham Somaroutu, Vijay Gopal
Designing contoured supersonic nozzles for high-speed wind tunnel facilities has traditionally relied on predefined expansion curves and Method of Characteristics (MoC) solutions patched across nozzle regions using curve-fitting techniques. These approaches require numerous sensitive inputs, including a predefined centerline flow distribution, where small inconsistencies can lead to nonphysical contours or poor exit-flow uniformity. This study presents a robust analytical method for designing a broad class of supersonic contoured nozzles using a constrained streamline-tracing approach. The method selects an appropriate streamline from a reference nozzle as the desired wall contour. The reference nozzle is a modified minimum-length configuration with a nonsingular acceleration profile, generated from a continuous MoC solution without patching or interpolation. Streamline selection criteria are formulated to avoid influences of gas centripetal acceleration, strong viscous interactions, sonic-line curvature effects near the throat, and excessive boundary-layer growth near the exit. After selecting the streamline as the inviscid contour, it is corrected for viscous effects using an integral compressible boundary-layer formulation. Numerical simulations were performed for contours designed using the proposed method and Sivells’ technique using the k–ω turbulence model. Test cases include high-Reynolds-number nozzles for Mach 1.8, 2.0, and 2.2, as well as a low-Reynolds-number case for Mach 4.0. An overall performance metric, ϕeff, is introduced to assess exit-flow quality by incorporating effective inviscid core area, flow distortion, and flow angularity. Results show that contours from the proposed method consistently outperform those from Sivells’ approach, with ϕeff values at the theoretical nozzle exit higher by a factor of 1.3–1.58, while retaining simplicity in implementation.
{"title":"A Robust Analytical Method for Designing Supersonic Contoured Nozzles Using Constrained Streamline-Tracing Approach","authors":"Sai Gowtham Somaroutu, Vijay Gopal","doi":"10.1016/j.ast.2026.111803","DOIUrl":"https://doi.org/10.1016/j.ast.2026.111803","url":null,"abstract":"Designing contoured supersonic nozzles for high-speed wind tunnel facilities has traditionally relied on predefined expansion curves and Method of Characteristics (MoC) solutions patched across nozzle regions using curve-fitting techniques. These approaches require numerous sensitive inputs, including a predefined centerline flow distribution, where small inconsistencies can lead to nonphysical contours or poor exit-flow uniformity. This study presents a robust analytical method for designing a broad class of supersonic contoured nozzles using a constrained streamline-tracing approach. The method selects an appropriate streamline from a reference nozzle as the desired wall contour. The reference nozzle is a modified minimum-length configuration with a nonsingular acceleration profile, generated from a continuous MoC solution without patching or interpolation. Streamline selection criteria are formulated to avoid influences of gas centripetal acceleration, strong viscous interactions, sonic-line curvature effects near the throat, and excessive boundary-layer growth near the exit. After selecting the streamline as the inviscid contour, it is corrected for viscous effects using an integral compressible boundary-layer formulation. Numerical simulations were performed for contours designed using the proposed method and Sivells’ technique using the <ce:italic>k</ce:italic>–<ce:italic>ω</ce:italic> turbulence model. Test cases include high-Reynolds-number nozzles for Mach 1.8, 2.0, and 2.2, as well as a low-Reynolds-number case for Mach 4.0. An overall performance metric, <ce:italic>ϕ</ce:italic><ce:inf loc=\"post\">eff</ce:inf>, is introduced to assess exit-flow quality by incorporating effective inviscid core area, flow distortion, and flow angularity. Results show that contours from the proposed method consistently outperform those from Sivells’ approach, with <ce:italic>ϕ</ce:italic><ce:inf loc=\"post\">eff</ce:inf> values at the theoretical nozzle exit higher by a factor of 1.3–1.58, while retaining simplicity in implementation.","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"95 1","pages":""},"PeriodicalIF":5.6,"publicationDate":"2026-02-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146146714","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 : 2026-02-10DOI: 10.1016/j.ast.2026.111889
Yongkang Zhao , Guangfeng An , Xianjun Yu , Baojie Liu , Dongbo Hao , Xi Nan
Next-generation variable-cycle engines impose stringent requirements on the operating range of compressor systems in terms of mass flow rate and pressure ratio. Variable stators provide an effective means to meet these requirements; however, rapidly and accurately determining the operating domain of multistage compressors with variable stators remains a major challenge. To address this issue, this paper proposes an efficient framework for extracting the operating domain of such compressors. First, an improved one-dimensional performance calculation strategy is developed, which preserves design-point accuracy while significantly enhancing prediction accuracy over a wide stator-angle adjustment range, reducing characteristic prediction errors by more than 50 %. Second, the determination of the operating domain is reformulated as the computation of an envelope surface enclosing performance scatter points across the full adjustment range, which simplifies data handling and facilitates the identification of operating-limit boundaries. Third, a rapid solution strategy for the operating domain is introduced, substantially reducing the computational cost. For a four-stage variable-stator compressor, the required computational effort is reduced to 6.8 % of the original cost, with the reduction becoming more pronounced as the number of adjustable stages increases. Throughout the entire operating domain, the efficiency prediction error remains below 10⁻⁶. The proposed method enables fast and accurate determination of the operating domain of multistage compressors with variable stators and provides an effective tool for operating-range analysis in variable-cycle engine applications.
{"title":"A fast method for determining the operating domain of multistage compressors with variable stators","authors":"Yongkang Zhao , Guangfeng An , Xianjun Yu , Baojie Liu , Dongbo Hao , Xi Nan","doi":"10.1016/j.ast.2026.111889","DOIUrl":"10.1016/j.ast.2026.111889","url":null,"abstract":"<div><div>Next-generation variable-cycle engines impose stringent requirements on the operating range of compressor systems in terms of mass flow rate and pressure ratio. Variable stators provide an effective means to meet these requirements; however, rapidly and accurately determining the operating domain of multistage compressors with variable stators remains a major challenge. To address this issue, this paper proposes an efficient framework for extracting the operating domain of such compressors. First, an improved one-dimensional performance calculation strategy is developed, which preserves design-point accuracy while significantly enhancing prediction accuracy over a wide stator-angle adjustment range, reducing characteristic prediction errors by more than 50 %. Second, the determination of the operating domain is reformulated as the computation of an envelope surface enclosing performance scatter points across the full adjustment range, which simplifies data handling and facilitates the identification of operating-limit boundaries. Third, a rapid solution strategy for the operating domain is introduced, substantially reducing the computational cost. For a four-stage variable-stator compressor, the required computational effort is reduced to 6.8 % of the original cost, with the reduction becoming more pronounced as the number of adjustable stages increases. Throughout the entire operating domain, the efficiency prediction error remains below 10⁻⁶. The proposed method enables fast and accurate determination of the operating domain of multistage compressors with variable stators and provides an effective tool for operating-range analysis in variable-cycle engine applications.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"174 ","pages":"Article 111889"},"PeriodicalIF":5.8,"publicationDate":"2026-02-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146153024","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}
扫码关注我们
求助内容：
应助结果提醒方式：
京公网安备 11010802042870号