Journal of Aircraft最新文献_第3页

Scale Effects in Wind Tunnel Testing: Extrapolation of the Drag Coefficient 风洞试验中的规模效应：阻力系数外推法

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2024-05-28 DOI: 10.2514/1.c037907

Lance W. Traub

引用次数: 0

Aerodynamic Modeling of a Missile Combining Transfer Learning and Dendritic Net 结合迁移学习和树枝状网的导弹空气动力学建模

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2024-05-14 DOI: 10.2514/1.c037865

Zijian Ni, Shiwei Chen, Zejun Zhu, Wei Wang

引用次数: 0

Actuator Surface Modeling of Rotors at the Ship–Helicopter Dynamic Interface 船舶-直升机动态界面上的旋翼致动器表面建模

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2024-05-13 DOI: 10.2514/1.c037034

Daniel Linton, Ben Thornber

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Performance Improvement of Winged Compound Helicopter Due to Differential Flap Deflections 差异襟翼挠度改善翼型复合直升机的性能

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2024-05-08 DOI: 10.2514/1.c037307

Hideaki Sugawara, Yasutada Tanabe, Masaharu Kameda

引用次数: 0

Machine Learning Models for Multirotor Performance Prediction 用于多旋翼飞行器性能预测的机器学习模型

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2024-05-06 DOI: 10.2514/1.c037460

Jason Cornelius, Sven Schmitz

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Propeller Ceiling Effect in Forward Flight 正向飞行中的螺旋桨升限效应

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2024-05-02 DOI: 10.2514/1.c037779

Jielong Cai, Sidaard Gunasekaran

{"title":"Propeller Ceiling Effect in Forward Flight","authors":"Jielong Cai, Sidaard Gunasekaran","doi":"10.2514/1.c037779","DOIUrl":"https://doi.org/10.2514/1.c037779","url":null,"abstract":"The study extends the investigation of the fixed-pitch small-scale propeller in the ceiling effect to forward flight conditions at different propeller incidence angles. Force-based experiments, phase-locked particle image velocimetry (PIV), and surface oil flow visualization were conducted on two APC propellers at the University of Dayton Low Speed Wind Tunnel. For propellers in edgewise flight, the power required at constant thrust decreases at small advance ratios for each <math altimg=\"eq-00001.gif\" display=\"inline\" overflow=\"scroll\"><mrow><mi>h</mi><mo>/</mo><mi>D</mi></mrow></math> and then increases with a further increase in the advance ratio. Tilting the propeller forward reduces the ceiling effect benefits in both thrust and power, particularly at higher advance ratios. Performance similarity in the propeller ceiling effect at different <math altimg=\"eq-00002.gif\" display=\"inline\" overflow=\"scroll\"><mrow><mi>h</mi><mo>/</mo><mi>D</mi></mrow></math> is observed, and a performance prediction method is proposed. Phase-locked PIV showed an increase in the propeller inflow angle in the ceiling effect at small advance ratios, resulting in higher thrust generation. This effect reduces with an increase in the advance ratio due to minimized interactions with the ceiling plate. Hence, the measured propeller in-ceiling-effect (ICE) propeller performance cannot represent the propeller ICE performance at a higher forward flight speed. Additionally, PIV and surface flow visualization indicated the presence of a stagnation point on the ceiling plate near the trailing side of the propeller disk at higher advance ratios, leading to a reduction in propeller thrust generation.","PeriodicalId":14927,"journal":{"name":"Journal of Aircraft","volume":"12 1","pages":""},"PeriodicalIF":2.2,"publicationDate":"2024-05-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140841618","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"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

Design Exploration of a Distributed Electric Propulsion Aircraft Using Explainable Surrogate Models 利用可解释代用模型探索分布式电力推进飞机的设计思路

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2024-05-02 DOI: 10.2514/1.c037848

Pramudita Satria Palar, Eric Nguyen Van, Nathalie Bartoli, Joseph Morlier

{"title":"Design Exploration of a Distributed Electric Propulsion Aircraft Using Explainable Surrogate Models","authors":"Pramudita Satria Palar, Eric Nguyen Van, Nathalie Bartoli, Joseph Morlier","doi":"10.2514/1.c037848","DOIUrl":"https://doi.org/10.2514/1.c037848","url":null,"abstract":"Distributed electric propulsion in aircraft design is a concept that involves placing multiple electric motors across the aircraft’s airframe. Such a system has the potential to contribute to sustainable aviation by significantly reducing greenhouse gas emissions, minimizing noise pollution, improving fuel efficiency, and encouraging the use of cleaner energy sources. This paper investigates the impact and relationship of turbo-electric propulsion component characteristics with three performance quantities of interest: lift-to-drag ratio, operating empty weight, and fuel burn. Using the small- and medium-range “DRAGON” aircraft concept, we performed design exploration enabled through the explainable surrogate model strategy. This work uses Shapley additive explanations to illuminate the dependencies of these critical performance metrics on specific turbo-electric propulsion component characteristics, offering valuable insights to inform future advancements in electric propulsion technology. Through global sensitivity analysis, the study reveals a significant impact of electrical power unit (EPU) power density on lift-to-drag ratio, alongside notable roles played by EPU-specific power and applied voltage. For operating empty weight, EPU-specific power and voltage are highlighted as critical factors, while turboshaft power-specific fuel consumption notably influences fuel burn. The analysis concludes by exploring the implications of the insights for the future development of turbo-electric propulsion technology.","PeriodicalId":14927,"journal":{"name":"Journal of Aircraft","volume":"90 1","pages":""},"PeriodicalIF":2.2,"publicationDate":"2024-05-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140841171","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"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

Integrated Three-Dimensional Airloads and Stresses on Lift-Offset Coaxial Rotors at Extreme Speeds 极速情况下升降偏置同轴转子上的综合三维空气载荷和应力

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2024-04-30 DOI: 10.2514/1.c037767

Mrinalgouda Patil, Anubhav Datta, Ravi Lumba, Buvana Jayaraman

引用次数: 0

Turbulent Airwake Estimation from Helicopter–Ship Wind-Tunnel Data 从直升机-船舶风洞数据中估算湍流气浪

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2024-04-17 DOI: 10.2514/1.c037526

Neda Taymourtash, Giuseppe Quaranta

{"title":"Turbulent Airwake Estimation from Helicopter–Ship Wind-Tunnel Data","authors":"Neda Taymourtash, Giuseppe Quaranta","doi":"10.2514/1.c037526","DOIUrl":"https://doi.org/10.2514/1.c037526","url":null,"abstract":"This paper presents a stochastic approach for modeling the turbulent airwake suitable for real-time simulation of the helicopter–ship dynamic interface. This approach relies on the measurements of unsteady loads collected during a wind-tunnel test campaign with a scaled helicopter operating over the deck of simple frigate shape 1. Power spectral densities of the measured aerodynamic loads combined with the estimated frequency response functions are used to find, through an optimization algorithm, a model of airwake spectra over the range of frequencies which mainly affects the pilot workload during shipboard operations. Then, a set of autoregressive filters is designed for every particular rotor position and wind-over-deck condition, so that when driven by white noise, the spectrum of the output will reproduce those obtained from the optimization. This approach is applied to three different tested wind directions and three rotor positions by implementing the autoregressive filters into the multibody model of the experimental rotor. Frequency response analysis of the aerodynamic loads demonstrates that the turbulent airwake model obtained from the experimental data can predict the unsteadiness of loads comparable to those measured in the wind tunnel across the bandwidth of interest for pilot activities. The identified airwake models could be applied to a full-scale model to simulate the unsteady loads effectively experienced by the helicopter during a ship landing flight.","PeriodicalId":14927,"journal":{"name":"Journal of Aircraft","volume":"73 1","pages":""},"PeriodicalIF":2.2,"publicationDate":"2024-04-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140612514","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"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

Airfoil Design Framework for Optimized Boundary-Layer Integral Parameters 优化边界层积分参数的机翼设计框架

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2024-04-17 DOI: 10.2514/1.c037713

Armando R. Collazo Garcia, Phillip J. Ansell

{"title":"Airfoil Design Framework for Optimized Boundary-Layer Integral Parameters","authors":"Armando R. Collazo Garcia, Phillip J. Ansell","doi":"10.2514/1.c037713","DOIUrl":"https://doi.org/10.2514/1.c037713","url":null,"abstract":"An airfoil design framework is introduced in which boundary-layer integral parameters serve as the driving design mechanism. The method consists of generating a parameterized pressure distribution capable of producing the desired boundary-layer characteristics for inverse design use. Additionally, by deduction from the Squire–Young theory, the method allows for the determination of the pressure distribution that results in the minimum theoretical drag. To assess this design framework, several airfoils were developed based on the mission requirements of the RQ-4B Global Hawk aircraft. Numerical results obtained using a viscous-inviscid solver of the integral boundary layer and Euler equations showed that the optimized airfoils achieved profile drag reductions of 9.06 and 6.00%, respectively, for <math altimg=\"eq-00001.gif\" display=\"inline\" overflow=\"scroll\"><mrow><mi>α</mi><mo>=</mo><mn>0</mn><mo>°</mo></mrow></math> and <math altimg=\"eq-00002.gif\" display=\"inline\" overflow=\"scroll\"><mrow><mi>L</mi><mo>/</mo><msub><mi>D</mi><mi>max</mi></msub></mrow></math> design points. A validation experimental campaign was also performed using the optimized CA5427-72 airfoil. The acquired data produced the expected pressure distribution characteristics and aerodynamic performance improvements, typifying the efficacy of the design framework.","PeriodicalId":14927,"journal":{"name":"Journal of Aircraft","volume":"166 1","pages":""},"PeriodicalIF":2.2,"publicationDate":"2024-04-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140612520","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"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