Aerospace Science and Technology最新文献_第10页

Robust adaptive control law design for enhanced stability of agriculture UAV used for pesticide spraying 设计鲁棒自适应控制法则，增强用于喷洒农药的农业无人机的稳定性

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-10-21 DOI: 10.1016/j.ast.2024.109676

Salman Ijaz , Yuhao Shi , Yasir Ali Khan , Maria Khodaverdian , Umair Javaid

{"title":"Robust adaptive control law design for enhanced stability of agriculture UAV used for pesticide spraying","authors":"Salman Ijaz , Yuhao Shi , Yasir Ali Khan , Maria Khodaverdian , Umair Javaid","doi":"10.1016/j.ast.2024.109676","DOIUrl":"10.1016/j.ast.2024.109676","url":null,"abstract":"<div><div>In precision agriculture, such as crop spraying, controlling UAVs presents various challenges such as variable payload, inertial coefficient variation, influence of external disturbances such as wind gusts, and uncertainties associated with the dynamics. To address these challenges, this paper proposes a hybrid control technique that combines higher-order integral sliding mode control, fast-terminal sliding mode control, and adaptive law. The objective is to mitigate the effects of variable payload, external disturbances, and uncertainties while maintaining the stability and performance of the UAV during spraying. Initially, a mathematical model is constructed for a coaxial octocopter UAV that is fitted with a spraying tank. This model takes into account the variation in mass and moment of inertia. Then, a two-loop control structure is employed to attain control of both the translational and rotational axis of the UAV. The numerical simulations are performed on a nonlinear model of the agricultural UAV system and compared with neural network based sliding mode control and robust adaptive backstepping control schemes. The robustness of the proposed scheme is tested in wind gusts and sensor measurement error conditions. Finally, hardware-in-loop simulations are performed using the Pixhawk Orange Cube flight controller to validate the real-time capability of the proposed scheme.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109676"},"PeriodicalIF":5.0,"publicationDate":"2024-10-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142552907","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Study on cryogenic cavitation and its temperature-pressure correlated characteristics of methane pump in rocket engine 火箭发动机甲烷泵的低温气蚀及其温压相关特性研究

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-10-21 DOI: 10.1016/j.ast.2024.109679

Yanpi Lin , Lei Wang , Fang Zhang , Xiaojun Li , Zuchao Zhu

{"title":"Study on cryogenic cavitation and its temperature-pressure correlated characteristics of methane pump in rocket engine","authors":"Yanpi Lin , Lei Wang , Fang Zhang , Xiaojun Li , Zuchao Zhu","doi":"10.1016/j.ast.2024.109679","DOIUrl":"10.1016/j.ast.2024.109679","url":null,"abstract":"<div><div>The harsh and complex working environment such as low temperature, high pressure and high speed in the turbopump brings great challenges to the working performance, operation stability and structural safety of the turbine pump device. In this research, the cryogenic cavitation of methane pump in liquid oxygen-methane rocket engine is studied by the combination of experiment and high-performance computing cluster numerical simulation. The unsteady flow calculation of the methane pump is carried out to reveal the cavitation and its temperature-pressure correlated characteristics of the methane pump in different operation conditions. A cryogenic cavitation model considering the thermal effect of cryogenic medium is established and the cryogenic cavitation simulation of methane pump is carried out. The hydraulic and cavitation performance experiments of methane pump are also performed. It is demonstrated that: 1) The volume fraction and cycle of cavitation in pump will decrease exponentially with the increase of inlet pressure. The cavitation cycle under low inlet pressure (0.146 MPa) is five times of that under high inlet pressure (0.3 MPa). 2) The decrease of inlet pressure will lead to the decrease of Strouhal number, which will weaken the unsteady cavitation effect of methane pump and enhance the influence of fluid inertia effect on cavitation. 3) Cavitation in inducer is mainly dominated by the backflow vortex cavitation (BVC) and the blade cavitation (BC) under lower inlet pressure condition, while the backflow vortex cavitation (BVC) and the tip vortex (TVC) cavitation are the main contribution in higher inlet pressure conditions. Through the study of cryogenic cavitation under harsh pump working conditions is benefit to reveal the cavitation mechanism of methane pump, and provide theoretical basis and technical support for the improvement design of turbopump.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109679"},"PeriodicalIF":5.0,"publicationDate":"2024-10-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142535233","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}

引用次数: 0

Adaptive control of nonlinear time-varying systems with unknown parameters and model uncertainties 具有未知参数和模型不确定性的非线性时变系统的自适应控制

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-10-21 DOI: 10.1016/j.ast.2024.109677

Zhenwei Ma , Qiufeng Wang

{"title":"Adaptive control of nonlinear time-varying systems with unknown parameters and model uncertainties","authors":"Zhenwei Ma , Qiufeng Wang","doi":"10.1016/j.ast.2024.109677","DOIUrl":"10.1016/j.ast.2024.109677","url":null,"abstract":"<div><div>This paper investigates the adaptive control problem for nonlinear time-varying systems with unknown parameters and model uncertainties. A novel class of switching functions is designed, and its construction method is detailed, along with a proof of the continuity of its <span><math><mi>n</mi><mo>−</mo><mn>1</mn></math></span> order derivatives. Two simple examples are provided to illustrate how the proposed congelation of variables method handles unknown high-frequency time-varying parameters in both the feedback and input paths. A new neural network control scheme is then developed, integrating an adaptive neural network controller with a robust controller. The smooth transition between these two controllers is ensured by the novel switching function, which guarantees global system stability. Furthermore, by combining the congelation of variables method with adaptive backstepping, a new adaptive tracking control scheme is proposed. This scheme effectively handles unknown high-frequency time-varying parameters while achieving asymptotic tracking of arbitrary reference signals. Simulation results show that the proposed novel adaptive control method delivers superior control accuracy while reducing energy consumption: it achieves an order of magnitude improvement over the traditional adaptive robust control method and two orders of magnitude improvement over the conventional sliding mode control method.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109677"},"PeriodicalIF":5.0,"publicationDate":"2024-10-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142552906","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}

引用次数: 0

Aeroelasticity of an aircraft wing with nonlinear energy sink 具有非线性能量沉降的飞机机翼的气动弹性

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-10-20 DOI: 10.1016/j.ast.2024.109684

I.P. Wall, M.R. Amoozgar, A.A. Popov

{"title":"Aeroelasticity of an aircraft wing with nonlinear energy sink","authors":"I.P. Wall, M.R. Amoozgar, A.A. Popov","doi":"10.1016/j.ast.2024.109684","DOIUrl":"10.1016/j.ast.2024.109684","url":null,"abstract":"<div><div>In this paper, the effectiveness of nonlinear energy sinks on enhancing aeroelastic stability and post-instability response of aircraft wings is investigated. The wing has two degrees of freedom in bending and torsion, and is modelled using an extended Euler-Bernoulli beam theory with hardening nonlinearity. A Nonlinear Energy Sink (NES) absorber is embedded inside the wing distributed along the wing span. The wing attached unsteady aerodynamic loads are simulated using the Wagner's indicial lift model. The structural dynamics of the wing are derived using Extended Hamilton's Principle and it is discretised using Galerkin's method. The NES mass is connected to the wing spar through a linear damper and nonlinear spring with a cubic stiffness nonlinearity. The coupled aeroelastic equations are then transformed to state space. Then, integrated numerically to resolve the bending and torsional response of the wing to study the impact of spanwise and chordwise positions of the embedded NES on flutter suppression and instability response enhancement. The results demonstrate that the NES is most efficient and is most sensitive to changes in the stiffness when placed at the wingtip. For a given chordwise location, it is found that there is a range of flow speeds over which the NES is most effective and reducing the chordwise offset lowers the speed of the peak efficiency range and moves it closer to the flutter speed. In addition, increasing the stiffness coefficient of the NES improves the efficiency of the device in the immediate post-flutter region. Two near optimum NES devices are proposed with a mass ratios of 1% (located at the wingtip) and 2.5% (located at 75% span). Both of these improve the flutter speed by 5%, and reduce the post-flutter response by 64.5% and 59.2%, respectively.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109684"},"PeriodicalIF":5.0,"publicationDate":"2024-10-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142534788","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

High precision aerodynamic heat prediction method based on data augmentation and transfer learning 基于数据增强和迁移学习的高精度空气动力热预测方法

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-10-19 DOI: 10.1016/j.ast.2024.109663

Ze Wang , Weiwei Zhang , Xu Wang , Shufang Song

{"title":"High precision aerodynamic heat prediction method based on data augmentation and transfer learning","authors":"Ze Wang , Weiwei Zhang , Xu Wang , Shufang Song","doi":"10.1016/j.ast.2024.109663","DOIUrl":"10.1016/j.ast.2024.109663","url":null,"abstract":"<div><div>Data-driven modeling methods have become one of the main technologies for predicting aerodynamic heat in hypersonic conditions. However, due to the limitations of wind tunnel experimental conditions, the spatial distribution of aerothermal wind tunnel experimental data is often sparse, and the sample size is relatively small. Furthermore, there is a lack of direct correlation in the aerodynamic heat distribution data among different shapes of vehicles, which poses challenges for constructing high-performance data-driven aerodynamic heat prediction models. To address these issues, this paper proposes a high-precision aerodynamic heat modeling and prediction method based on data augmentation and transfer learning. First, integrating the concept of data fusion, we propose to enhance the sparse aerothermal wind tunnel experimental data by using deep neural networks and introducing low-precision numerical computation results. Next, based on the close physical correlation between boundary layer outer edge information and wall surface aerodynamic heat, we construct the aerodynamic heat prediction model ED-ResNet using a double-series residual neural network. Finally, by fine-tuning the ED-ResNet model for transfer learning, high-precision predictions of aerothermal wind tunnel experimental results for different shaped vehicles are achieved under small sample conditions. Verification using hypersonic double-ellipsoid, blunt cone, and blunt bicone shows that after data augmentation, the prediction error of the aerodynamic heat prediction model is significantly reduced to 1/3 of that when data augmentation is not used. Moreover, through transfer learning, the model effectively leverages existing hypersonic double-ellipsoid aerothermal wind tunnel experimental data to achieve high-precision predictions of aerodynamic heat distribution for blunt cone and blunt double cone under different incoming flow conditions, with normalized root mean square error(NRMSE) maintained below 10 %.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109663"},"PeriodicalIF":5.0,"publicationDate":"2024-10-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142552903","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}

引用次数: 0

A quantitative three-dimensional inverse design rule based on cross-flow control of profiled end wall 基于异型端壁横流控制的定量三维逆向设计规则

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-10-19 DOI: 10.1016/j.ast.2024.109670

Hanwen Guo , Donghai Jin , Jiancheng Zhang , Hao Yu , Yucheng Dai

{"title":"A quantitative three-dimensional inverse design rule based on cross-flow control of profiled end wall","authors":"Hanwen Guo , Donghai Jin , Jiancheng Zhang , Hao Yu , Yucheng Dai","doi":"10.1016/j.ast.2024.109670","DOIUrl":"10.1016/j.ast.2024.109670","url":null,"abstract":"<div><div>Profiled end wall provides a novel and effective solution for end wall flow control in turbines and compressors. However, the application of profiled end walls in compressors still lacks quantitative design rules. This paper presents a quantitative design rule for end wall profiling based on a three-dimensional inverse method and numerically validates it on a highly loaded compressor cascade. The current inverse method can solve the corresponding end wall shape from a given end wall pressure distribution, but the determination of the end wall pressure distribution heavily relies on empirical knowledge. This study establishes a model between streamline curvature and cross-passage pressure gradient (CPG) through the circumferential equilibrium equation in the S1 stream surface, thereby providing a quantitative basis for determining the end wall pressure distribution. The quantitative design rule proposed in this paper is expressed as follows: at the axial position where the separation begins on the suction surface (SS), within the range of 0.1–0.2 pitch away from the SS, the end wall boundary layer fluid with a higher velocity than the corner region average velocity should possess the same streamline curvature as the fluid within the viscous sublayer. The inverse-designed profiled end wall using the quantitative design rule enhances the local cross-flow near the SS by imposing a stronger CPG, thus encouraging the end wall boundary layer fluid with relatively higher momentum to arrive at the SS earlier and enhancing the radial migration on the SS. Consequently, the intensified cross-flow entrains relatively higher momentum into the corner region, while the enhanced radial migration drives the low-momentum fluid away from the corner region towards the midspan. Finally, the inverse-designed profiled end wall reduces the half-span mass-flow-weighted average loss by 4.3%.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109670"},"PeriodicalIF":5.0,"publicationDate":"2024-10-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142552904","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}

引用次数: 0

Quaternion-based non-singular nonlinear impact angle guidance for three-dimensional engagements 基于四元数的三维交战非矢量非线性撞击角制导

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-10-18 DOI: 10.1016/j.ast.2024.109657

Prajakta Surve, Arnab Maity, Shashi Ranjan Kumar

引用次数: 0

An optimal parameterized Newton-type structure-preserving doubling algorithm for impact angle guidance-based 3D pursuer/target interception engagement 基于撞击角制导的三维追击者/目标拦截交战的最优参数化牛顿式保结构倍增算法

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-10-18 DOI: 10.1016/j.ast.2024.109674

Tsung-Ming Huang , Yueh-Cheng Kuo , Wen-Wei Lin , Chin-Tien Wu

{"title":"An optimal parameterized Newton-type structure-preserving doubling algorithm for impact angle guidance-based 3D pursuer/target interception engagement","authors":"Tsung-Ming Huang , Yueh-Cheng Kuo , Wen-Wei Lin , Chin-Tien Wu","doi":"10.1016/j.ast.2024.109674","DOIUrl":"10.1016/j.ast.2024.109674","url":null,"abstract":"<div><div>The proposed strategy, finite-time state-dependent Riccati equation (FT-SDRE)-based impact angle guidance, is generally employed to solve the 3D pursuer/target interception model with fixed lateral accelerations. This article expands its application to a general scenario where the lateral acceleration of a target may change. To achieve this, we approximate the accelerations of the azimuth and elevation angles of the target in the inertial frame via second-order finite difference schemes and develop a high-performance FT-SDRE algorithm with structure-preserving doubling algorithms (SDAs). As a result, the update frequency of the controller can be increased, and better guidance of the pursuer can be obtained to address the high maneuverability of the target during the entire interception procedure. At every state of the FT-SDRE, a modified Newton–Lyapunov method is employed to solve the continuous algebraic Riccati equation (CARE), and a new simplified SDA with adaptive optimal parameter selection is proposed for solving the associated Lyapunov equation. Our numerical results demonstrate that the FT-SDRE algorithm accelerated by our proposed methods is approximately three times faster than the FT-SDRE algorithm, in which the MATLAB functions <strong>icare</strong> and <strong>lyap</strong> are used to solve the CARE and the Lyapunov equation, respectively, throughout the entire interception procedure. In other words, the control frequency can be increased threefold. In our benchmark cases where the target maneuvers with nonlinear lateral acceleration, the target can be intercepted earlier via the proposed FT-SDRE algorithm.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109674"},"PeriodicalIF":5.0,"publicationDate":"2024-10-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142534786","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}

引用次数: 0

Investigation on ignition enhancement characteristics by high-energy spark in a scramjet combustor under low flight Mach conditions 低飞行马赫数条件下高能火花在扰流喷气燃烧器中的点火增强特性研究

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-10-18 DOI: 10.1016/j.ast.2024.109681

Huifeng Miao , Zhibo Zhang , Xing Zheng , Lan Zhang , Yun Wu , Yinghong li

{"title":"Investigation on ignition enhancement characteristics by high-energy spark in a scramjet combustor under low flight Mach conditions","authors":"Huifeng Miao , Zhibo Zhang , Xing Zheng , Lan Zhang , Yun Wu , Yinghong li","doi":"10.1016/j.ast.2024.109681","DOIUrl":"10.1016/j.ast.2024.109681","url":null,"abstract":"<div><div>Ignition characteristics of the long electrode distance high-energy spark igniter (LHSI) in a cavity-stabilized scramjet combustor at low flight Mach has been numerically and experimentally investigated and compared with those of conventional lower energy spark igniter (SI). The effects of ignition and injection schemes on ignition performance were analyzed and the enhancement of greater spark energy were verified. The results show that the widest ignition boundary of SI is observed when the kerosene is injected in far field due to the sufficient evaporation of kerosene droplets and the disturbance caused by upstream cavity. Due to the greater energy deposition by LHSI, the ignition performance is markedly improved and the ignition boundary of combustor is extended from 0.131–0.148 to 0.091–0.224 under the scheme of I1+L2. The increased energy deposition of spark plasma ignites more combustible mixture and enhances the initial combustion, leading to a larger high-temperature zone. This is crucial for ensuring the survival of the flame kernel against dissipation of airflow in the scramjet combustor operating at low fight Mach numbers due to the short duration of spark discharge.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109681"},"PeriodicalIF":5.0,"publicationDate":"2024-10-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142534787","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}

引用次数: 0

A comprehensive investigation of the effect of hole diameter and number on film cooling performance of rotating blade leading edge 孔径和孔数对旋转叶片前缘薄膜冷却性能影响的综合研究

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-10-18 DOI: 10.1016/j.ast.2024.109659

Meng Gu , Hai-wang Li , Zhi-yu Zhou , Gang Xie , Song Liu , Yu-zhu Lou

{"title":"A comprehensive investigation of the effect of hole diameter and number on film cooling performance of rotating blade leading edge","authors":"Meng Gu , Hai-wang Li , Zhi-yu Zhou , Gang Xie , Song Liu , Yu-zhu Lou","doi":"10.1016/j.ast.2024.109659","DOIUrl":"10.1016/j.ast.2024.109659","url":null,"abstract":"<div><div>The combined effect of film hole number and diameter on the film cooling were investigated on the rotating blade leading edge by using experimental and numerical methods. The film cooling performance was obtained by pressure sensitive paint technique under rotational condition. To better understand the experimental results, the flow fields obtained from numerical simulation were also analyzed. The effects of hole length-to-diameter ratio (L/<em>d</em> = 2.5/5/7.5), hole number (<em>N</em> = 7/9/10/11/13), hole diameter(<em>d</em> = 0.64∼1.26 mm), Hole to hole pitch, (P/<em>d</em> = 6.3∼9.2) and hole exit area (A<sub>hole</sub>/A<sub>LE</sub>=4 %-14 %) on the film cooling performance are investigated. Five blowing ratios are also employed (<em>M</em> = 0.5 to 2.0). The results indicate that the hole length-to-diameter ratios (L/<em>d</em> = 2.5∼7.5) have a negligible influence on the film cooling effectiveness. Both the film hole number (<em>N</em> = 10/13) and the hole diameter (<em>d</em> = 0.64/0.75 mm) monotonically affect the film cooling performance under each blowing ratios. However, a comprehensive study indicates that there is a significant quadratic correlation between the area-averaged cooling effectiveness and the total film hole exit area for different combinations of hole number and diameter. Meanwhile, there is an optimal film hole exit area on the leading edge and it increases as the blowing ratio or mass flow rate increases.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109659"},"PeriodicalIF":5.0,"publicationDate":"2024-10-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142552905","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}

引用次数: 0