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Aerodynamic state estimation from sparse sensor data by pairing Bayesian statistics with transition networks 基于贝叶斯统计与过渡网络的稀疏传感器空气动力状态估计
Pub Date : 2022-01-03 DOI: 10.2514/6.2022-1669
F. Kaiser, G. Iacobello, D. Rival
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引用次数: 1
Laser Ignition of Solid Propellants Using Energetic nAl-PVDF Optical Sensitizers 用高能nAl-PVDF光敏剂激光点燃固体推进剂
Pub Date : 2022-01-03 DOI: 10.2514/6.2022-1744
Kyle E. Uhlenhake, Mateo Gomez, Diane N. Collard, M. Örnek, S. Son
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引用次数: 4
Adaptive Manual Control: a Predictive Coding Approach 自适应人工控制:一种预测编码方法
Pub Date : 2022-01-03 DOI: 10.2514/6.2022-2448
Lorenzo Terenzi, P. Zaal, D. Pool, M. Mulder
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引用次数: 2
Aluminum Combustion in a Shock Tube at High Pressure 高压下激波管内铝的燃烧
Pub Date : 2022-01-03 DOI: 10.2514/6.2022-0637
K. Daniel, K. Lynch, C. Downing, J. Wagner
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引用次数: 1
Wind Turbine Efficiency Enhancement by CoFlow Jet Airfoil CoFlow喷气翼型提高风力涡轮机效率
Pub Date : 2022-01-03 DOI: 10.2514/6.2022-1787
Yan Ren, Kewei Xu, Gecheng Zha
The aerodynamic performance and flow structures of a high efficiency Co-Flow Jet (CFJ) wind turbine is studied in this paper. CFJ is a zero-net-mass-flux active flow control method that dramatically increases airfoil lift coefficient and suppresses flow separation at a low energy expenditure. The 3D Reynolds Averaged Navier-Stokes (RANS) equations with one-equation Spalart-Allmaras (SA) turbulence model are solved to simulate the 3D flows of the wind turbines. The CFJ-Wind Turbine in this paper utilizes a new CFJ-NACA6421 airfoil, but the twist and chord distributions are the same as those of the NREL 5.029m radius Phase VI wind turbine, which is used as the baseline turbine for comparison. The predicted power coefficient of the baseline turbine agrees excellently with the measured one by a small deviation of 1.1%. The predicted surface pressure distributions are also in very good agreement with the experiment. The CFJ injection and suction slots are implemented along the blade span to achieve CFJ active flow control. The study indicates that the CFJ active flow control can significantly enhance the power output of a well optimized conventional wind turbine at its design flow speed. The results show that the flow field around the CFJ wind turbine blade surface suppressed flow separation near the blade root region. The parametric study show that the optimum jet momentum coefficient C µ is 0.02. At the same design RPM of the baseline blade with a tip speed ratio of 5.4 and freestream speed of 7 m/s, the CFJ turbine achieves a power coefficient of 0.475, a 29.4% improvement over the baseline turbine’s design point efficiency. At a higher RPM with the tip speed ratio of 6.3, the CFJ wind turbine net power coefficient is 0.492, which presents 34.1% improvement comparing to the NREL Phase VI wind turbine at its design point. The work on more parametric study is in progress to further optimize the design.
本文研究了高效共流射流风力机的气动性能和流动结构。CFJ是一种零净质量通量的主动流动控制方法,能以较低的能量消耗显著提高翼型升力系数,抑制流动分离。采用单方程Spalart-Allmaras (SA)湍流模型求解三维Reynolds平均Navier-Stokes (RANS)方程,模拟风力机的三维流动。本文的cfj -风力机采用了一种新的CFJ-NACA6421翼型,但扭曲和弦分布与NREL 5.029m半径的六期风力机相同,作为基准涡轮机进行比较。预测的基准涡轮功率系数与实测值吻合良好,误差仅为1.1%。预测的表面压力分布也与实验结果吻合得很好。CFJ喷注槽和抽吸槽沿叶跨布置,实现CFJ主动流动控制。研究表明,CFJ主动流量控制可以显著提高优化后的常规风力机在设计风速下的输出功率。结果表明,CFJ风力机叶片表面周围的流场抑制了叶片根部附近的流动分离。参数化研究表明,最佳射流动量系数Cµ为0.02。在基线叶片相同设计转数下,叶尖速比为5.4,自由流速度为7 m/s, CFJ涡轮的功率系数为0.475,比基线涡轮的设计点效率提高了29.4%。在较高转速下,叶尖速比为6.3时,CFJ风机净功率系数为0.492,比NREL六期风机设计点提高34.1%。更多的参数化研究工作正在进行中,以进一步优化设计。
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引用次数: 1
Low-Order Modeling of Unsteady Flow Around Airfoils with Rounded Trailing Edges 圆形尾缘翼型绕流非定常流场的低阶建模
Pub Date : 2022-01-03 DOI: 10.2514/6.2022-1668
Yi Tsung Lee, Kiran Ramesh, Ashok Gopalarathnam
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引用次数: 0
The Influence of the Computational Mesh on the Prediction of Vortex Interactions about a Generic Missile Airframe 计算网格对某型导弹机体涡相互作用预测的影响
Pub Date : 2022-01-03 DOI: 10.2514/6.2022-1176
E. Dikbaş, C. Schnepf, M. Tormalm, Michael Anderson, S. Shaw, J. Despirito, G. Loupy, G. Barakos, K. Boychev, C. Toomer, O. Baran
A research program has been underway for four years to study vortex interaction aerodynamics that are relevant to military air vehicle performance. The program has been conducted under the auspices of the NATO Science and Technology Organization (STO), Applied Vehicle Technology (AVT) panel by a Task Group with the identification of AVT-316. The Missile Facet of this group has concentrated their work on the vortical flow field around a generic missile airframe and its prediction via computational methods. This paper focuses on mesh-related effects and RANS simulations. Simulated vortex characteristics
一个研究涡旋相互作用空气动力学与军用飞行器性能相关的研究项目已经进行了四年。该项目是在北约科技组织(STO)应用车辆技术(AVT)小组的主持下进行的,任务小组的编号为AVT-316。导弹方面的研究主要集中在通用导弹机身周围的涡旋流场及其计算方法的预测。本文主要研究网格相关效应和RANS仿真。模拟涡特性
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引用次数: 1
A framework for campaign level asteroid mining pre-feasibility study 战役级小行星采矿预可行性研究框架
Pub Date : 2022-01-03 DOI: 10.2514/6.2022-2583
Ruida Xie, S. Saydam, A. Dempster
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引用次数: 2
Reduced-Order Aerodynamics with the Method of Integrated Circulation 集成循环法的降阶空气动力学
Pub Date : 2022-01-03 DOI: 10.2514/6.2022-0005
Vivek Ahuja, R. Hartfield
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引用次数: 5
Structural Optimization of Regeneratively Cooled Rotating Detonation Rocket Engines 再生冷却旋转爆轰火箭发动机结构优化
Pub Date : 2022-01-03 DOI: 10.2514/6.2022-0092
E. Jørgensen, Z. Cordero, David M. Vaccaro
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引用次数: 0
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AIAA SCITECH 2022 Forum
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