Journal of Aircraft最新文献_第4页

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

Fluid–Structure Coupled Analysis of Maneuver Load Alleviation on a Large Transport Aircraft 大型运输机操纵载荷减轻的流固耦合分析

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2024-04-11 DOI: 10.2514/1.c037648

Christian Breitenstein, Jens Müller, Marco Hillebrand, Malte Woidt, Matthias Haupt, Rolf Radespiel

引用次数: 0

Correlation of High-Speed Tiltrotor Stability Predictions with Test Data and Parametric Study 高速倾转旋翼机稳定性预测与测试数据的相关性及参数研究

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2024-04-05 DOI: 10.2514/1.c037807

Seyhan Gul, Hyeonsoo Yeo

{"title":"Correlation of High-Speed Tiltrotor Stability Predictions with Test Data and Parametric Study","authors":"Seyhan Gul, Hyeonsoo Yeo","doi":"10.2514/1.c037807","DOIUrl":"https://doi.org/10.2514/1.c037807","url":null,"abstract":"High-speed stability of tiltrotor was studied. The University of Maryland’s Maryland Tiltrotor Rig (MTR) was chosen for the analysis due to availability of properties and test data, and its interesting high-stability behavior observed in the Glenn L. Martin wind tunnel in August 2022. A Rotorcraft Comprehensive Analysis System (RCAS) model of the MTR gimbaled hub was built in addition to the University of Maryland Advanced Rotorcraft Code-II (UMARC-II) model from previous work. The objective is threefold: i) validate RCAS tiltrotor stability predictions, ii) shed light on the high-stability behavior of the MTR, and iii) find ways to lower the instability speed of the MTR for future wind tunnel tests. Trim collective for freewheeling and stability predictions were compared with wind tunnel test data up to 200 knots. RCAS and UMARC-II predictions showed good agreement with each other and the test data. Predictions show that MTR is stable up to 215 knots (490-knots full-scale flight) although the wing is only 18% thick (current technology is 23%). A parametric study was carried out. The impact of wing stiffness, pitch-flap coupling (<math altimg=\"eq-00001.gif\" display=\"inline\" overflow=\"scroll\"><mrow><msub><mi>δ</mi><mn>3</mn></msub></mrow></math> angle), lag stiffness, blade chord, number of blades, pylon mass, pylon center of gravity (c.g.), pylon location, and rotor speed was studied. MTR’s pylon c.g. is unconventionally behind the wing elastic axis. It was found that this significantly improved stability. This behavior is not specific to MTR; full-scale aircraft stability can also be improved by moving the pylon c.g. backward if wing beam is the least stable mode. A combination of forward pylon c.g., reduced rotor speed, and increased blade chord reduced the instability speed by more than 55 knots to near 160 knots, helping researchers obtain high-quality test data in the upcoming Glenn L. Martin wind tunnel tests.","PeriodicalId":14927,"journal":{"name":"Journal of Aircraft","volume":"55 1","pages":""},"PeriodicalIF":2.2,"publicationDate":"2024-04-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140602888","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

Three-Dimensional Spatial Atmospheric Turbulence Generation Method for Aerial Refueling Flight Simulation 用于空中加油飞行模拟的三维空间大气湍流生成方法

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2024-04-05 DOI: 10.2514/1.c037792

Xiangrui Meng, Zhibin Li, He Wang, Deping He

引用次数: 0

Individual Blade Control Approach for Active Vibration Suppression of a Lift-Offset Coaxial Rotorcraft 用于主动抑制升偏式同轴旋翼机振动的单桨控制方法

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2024-04-05 DOI: 10.2514/1.c037715

Hyun Seong Hong, Kyun Dong Kim, Nam Sung Jung

引用次数: 0

Reduced-Order Model for Supersonic Transport Takeoff Noise Scaling with Cruise Mach Number 超音速运输起飞噪声随巡航马赫数缩放的降阶模型

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2024-04-03 DOI: 10.2514/1.c037633

Laurens J. A. Voet, Prakash Prashanth, Raymond L. Speth, Jayant S. Sabnis, Choon S. Tan, Steven R. H. Barrett

引用次数: 0

Experimental and Computational Investigation of Rotor Noise in Hover 悬停时转子噪声的实验和计算研究

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2024-03-31 DOI: 10.2514/1.c037039

Chloe Johnson, Jayant Sirohi, George Jacobellis, Rajneesh Singh

引用次数: 0

Brake-Induced Landing Gear Walk Vibration Analysis and Suppression Method Research 制动引起的起落架行走振动分析与抑制方法研究

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2024-03-25 DOI: 10.2514/1.c037783

Zhuangzhuang Wang, Xiaochao Liu, Pengyuan Qi

引用次数: 0

Numerical Investigation by Applying Microballoon Actuators on High-Altitude Propeller 在高空螺旋桨上应用微气球致动器的数值研究

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2024-03-25 DOI: 10.2514/1.c037492

Zhengyu Qu, Ying Nie, Yanchu Yang

{"title":"Numerical Investigation by Applying Microballoon Actuators on High-Altitude Propeller","authors":"Zhengyu Qu, Ying Nie, Yanchu Yang","doi":"10.2514/1.c037492","DOIUrl":"https://doi.org/10.2514/1.c037492","url":null,"abstract":"Microballoon actuators as a potential active flow control device have been studied for years. However, most studies have relied on experimental methods to investigate its effects. In this paper, we utilized the numerical method of steady-state RANS to explore the feasibility of applying microballoon actuators to suppress flow separation on a wing section and a high-altitude propeller. The geometric design, including shapes and positions for microballoons, is introduced, and these microballoons are fully resolved for the numerical models to better assess the influence of sensitive parameters. The turbulent model used in simulations is well validated in comparison with experimental data. In the wing section model, computational results show that at <math altimg=\"eq-00001.gif\" display=\"inline\" overflow=\"scroll\"><mrow><mi>R</mi><mi>e</mi><mo>=</mo><mn>2</mn><mo>×</mo><msup><mn>10</mn><mn>5</mn></msup></mrow></math>, placing nonrotation microballoons close to the separation point can suppress separation bubbles and decrease drag by 12% before the stall angle of attack. In the propeller model, computational results show that placing a microballoon actuator array with a proper dimension and position on the blade can also effectively suppress the crossflow separation appearing at the trailing edge. At a rotational speed of 450 rpm, the efficiency enhancement can reach a maximum of 1.6%.","PeriodicalId":14927,"journal":{"name":"Journal of Aircraft","volume":"17 1","pages":""},"PeriodicalIF":2.2,"publicationDate":"2024-03-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140300557","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

Methodology for Evaluating a Distributed Variable-Camber Trailing-Edge System in Preliminary Aircraft Design 在飞机初步设计中评估分布式变腔拖曳刃系统的方法学

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2024-03-19 DOI: 10.2514/1.c037145

Ralph Stephan, Nicolas Schneiders, Gerrit Weber, Florian Schueltke, Eike Stumpf, Fabian Peter

引用次数: 0