2018 Flow Control Conference最新文献

Correction: Reduced-Order Models for Feedback Control of Transient Energy Growth 修正:瞬态能量增长反馈控制的降阶模型

2018 Flow Control Conference Pub Date : 2018-06-25 DOI: 10.2514/6.2018-3690.C1

Aniketh Kalur, Maziar S. Hemati

引用次数: 1

Correction: Preliminary Experimental Study on Closed-loop Flow Separation Control Utilizing Deep Q-Network over Fixed Angle-of-Attack Airfoil 修正:基于深q网络的固定迎角翼型闭环流分离控制的初步实验研究

2018 Flow Control Conference Pub Date : 2018-06-25 DOI: 10.2514/6.2018-3522.C1

Satoshi Shimomura, S. Sekimoto, Hiroaki Fukumoto, A. Oyama, K. Fujii, H. Nishida

引用次数: 0

Correction: Biomimetic Tubercle Leading-Edge Airfoils in Transitional Reynolds Number Regime 修正:过渡雷诺数下的仿结核型前缘翼型

2018 Flow Control Conference Pub Date : 2018-06-25 DOI: 10.2514/6.2018-4250.C1

Keshav Vedula, B. Cetegen, Joshua Madore, M. Bellinger

引用次数: 0

Correction: Response of a Laminar Separation Bubble to Zero-Net Mass Flux Actuation 修正:层流分离气泡对零净质量通量驱动的响应

2018 Flow Control Conference Pub Date : 2018-06-25 DOI: 10.2514/6.2018-4018.C1

Wen Wu, J. Seo, C. Meneveau, R. Mittal

引用次数: 0

Correction: Non-Equilibrium Effects of Interaction of Laser Discharge with Hemisphere-Cylinder in Supersonic Flow 修正:超声速流动中激光放电与半球-圆柱体相互作用的非平衡效应

2018 Flow Control Conference Pub Date : 2018-06-25 DOI: 10.2514/6.2018-3757.C1

Nadia Kianvashrad, D. Knight

引用次数: 3

Withdrawal: On the role of trailing edge geometry in cavity flow control 摘要:关于尾缘几何形状在空腔流动控制中的作用

2018 Flow Control Conference Pub Date : 2018-06-25 DOI: 10.2514/6.2018-3527.C1

Qiong Liu, Francisco Gómez

引用次数: 0

Simulations of Plasma Flow Control Strategies for Trailing Edge Separation 后缘分离等离子体流动控制策略的仿真

2018 Flow Control Conference Pub Date : 2018-06-24 DOI: 10.2514/6.2018-3524

Jennifer A. Franck, J. Cooney, N. Fine

引用次数: 1

Mitigation of Laminar Separation Flutter Using Plasma-Based Actuators 利用等离子体作动器缓解层流分离颤振

2018 Flow Control Conference Pub Date : 2018-06-24 DOI: 10.2514/6.2018-3523

C. Barnes, M. Visbal

引用次数: 3

Experimental Study of Flow Field Airfoil with Synthetic Jets for Flow Separation Control 合成射流流场翼型流动分离控制实验研究

2018 Flow Control Conference Pub Date : 2018-06-24 DOI: 10.2514/6.2018-3686

D. Wirtz, H. Hoeijmakers

{"title":"Experimental Study of Flow Field Airfoil with Synthetic Jets for Flow Separation Control","authors":"D. Wirtz, H. Hoeijmakers","doi":"10.2514/6.2018-3686","DOIUrl":"https://doi.org/10.2514/6.2018-3686","url":null,"abstract":"The flow over a wing or a deployed flap of a wing should remain attached to the surface; otherwise its aerodynamic performance will decrease drastically. Flow separation control aims at affecting the flow by actively delaying flow separation and thus improving the aerodynamic performance of the wing. In the present study synthetic jet actuators (SJA’s) have been applied for flow separation control in the case of a 2D wing with a chord of 165 mm and a span of 455 mm with a NACA0018 airfoil section. The SJA’s employed feature a piezo-electric disk inside a cavity and an exit slot of a span of 30 mm and a width of 0.25 mm. First the performance of a stand-alone SJA has been investigated in order to replicate the promising results found by the University of Florida for the present SJA design. Subsequently, a configuration with ten of these SJA’s integrated in the 2D NACA0018 wing has been considered. The jet from the SJA’s is directed tangentially to the surface of the airfoil. During the in-stroke of the actuator, air from the surroundings is ingested through the slot into the cavity, while during the out-stroke air is blown through the slot out of the cavity. The maximum peak velocity generated for a range of actuation frequencies of the integrated synthetic jets, have been measured, using a hot-wire anemometry (HWA) setup, first in quiescent air. These HWA results for the velocity field induced by the SJA’s have been compared with analytical results for a wall jet. In the next step the aerodynamic performance of the wing with ten SJA’s has been investigated inside a wind-tunnel at a free-stream velocity of 25 m/s, corresponding to a Reynolds number of 273,000. These measurements of the lift have been performed for a range of actuation frequencies and ratios of jet velocity and free-stream velocity. Finally, HWA measurements have been performed for a number of chord-wise positions, for a number of angles of attack, at a free-stream velocity of 25 m/s.","PeriodicalId":144668,"journal":{"name":"2018 Flow Control Conference","volume":"33 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132060138","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Flow Dynamics Effected by Active Flow Control in an Offset Diffuser 主动流动控制对偏置扩散器流动动力学的影响

2018 Flow Control Conference Pub Date : 2018-06-24 DOI: 10.2514/6.2018-4024

Travis J. Burrows, B. Vukasinovic, A. Glezer

{"title":"Flow Dynamics Effected by Active Flow Control in an Offset Diffuser","authors":"Travis J. Burrows, B. Vukasinovic, A. Glezer","doi":"10.2514/6.2018-4024","DOIUrl":"https://doi.org/10.2514/6.2018-4024","url":null,"abstract":"Total pressure distortions at the aerodynamic interface plane (AIP) of an aggressive double-offset diffuser that are induced by the formation of secondary vortices coupled with internal flow separation domains are mitigated by fluidic-based flow control. The presence of the secondary counter-rotating streamwise vortex pairs that form at each diffuser turn induces concentrations of total pressure deficit at the AIP by advecting low-momentum fluid from the wall region into the core flow. The effectiveness of fluidic actuation for suppression of the AIP distortions is demonstrated by implementing actuator arrays at the downstream diffuser turn that leads to over 60% reduction in the average circumferential distortion. Spectral and POD analyses of high-speed, time-resolved total pressure measurements at the AIP indicate that these counter-rotating vortex pairs are unstable exhibiting a frequency band centered about 1 kHz. The actuation alters the spectral content of the pressure fluctuations and leads to their broadband suppression that includes the unstable frequency band of the secondary vortices. The stabilization of the total pressure oscillations is reflected in suppression of not only time-averaged total pressure distortion, but it also reduces a spread of instantaneous distortion about its mean. Consequently, the peak instantaneous flow distortion is reduced by 25%.","PeriodicalId":144668,"journal":{"name":"2018 Flow Control Conference","volume":"12 3","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132285952","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 6