Mechanisms for shock wave boundary layer interaction control using surface arc plasma actuators array
-
摘要:
为了获得阵列表面电弧控制激波/附面层干扰不稳定性机理，开展了高频激励和低频激励的实验研究。综合运用高速纹影、动态压力等先进测试手段和分析方法，揭示阵列电弧等离子体激励的热效应和涡效应特性。结合流动显示和壁面动态压力脉动，深度揭示了控制过程。更为关键的，因为高频激励模式下的激励器处于低功耗状态，这样可以提供稳定的控制效果。基于动态压力频谱分析，发现高频激励下低频不稳定性能量的占比降低12.2%。结合纹影显示，获得高频激励下的涡效应主导机制。
Abstract:In order to reveal the control mechanism on shock wave/boundary layer unsteadiness，experiments were performed by using surface arc plasma actuators array based on both high⁃frequency and low frequency actuation.Advanced testing and analytical methods，including high⁃speed schlieren and dynamic pressure，were applied to reveal the thermal and vortex characteristic.The combined results of flow visualization and fluctuating wall pressure provided a valuable insight into the controlling process.More importantly，because of high⁃frequency actuation mode operating at a relatively low energy expense，this made it possible to achieve a stable control effect.Based on the reported results of the statistical analysis dynamic pressure，the percentage of the energy for low⁃frequency unsteadiness detected by spectra of pressure reduced by 12.2% at high⁃frequency forcing.Combined with schlieren display，a mechanism of shock wave boundary layer interaction control dominated by vortex effect can now be summarized.
-
图 2 激励与激波相互作用示意图
Figure 2. Schematic of the interaction between plasma actuation and shock wave
图 4 涡对激波附面层作用的原理图
Figure 4. Schematic diagram for the effect of vortices on shock wave boundary layer interaction
图 8 低频激励条件下单次脉冲的电压⁃电流曲线
Figure 8. voltage and current trajectory for a single pulse at low⁃frequency mode
图 11 高频激励下单次脉冲的电压电流曲线
Figure 11. Voltage and current trajectory for a single pulse at high⁃frequency actuation
-
[1] BARTER J W,DOLLING D S.Reduction of fluctuating pressure loads in shock/boundary layer interactions using vortex generators:Part 1[J].AIAA Journal,2014,33（10）:1842⁃1849. [2] LI Yinghong,WU Yun.Research progress and outlook of flow control and combustion control using plasma actuation[J].Scientia Sinica Technologica,2020,50（10）:1252⁃1273. [3] ZHU Yifei,WU Yun,JIA Min,et al.Influence of positive slopes on ultrafast heating in an atmospheric nanosecond⁃pulsed plasma synthetic jet[J].Plasma Sources Science and Technology,2015,24（1）:15007⁃15019. [4] IM S,DO H,CAPPELLI M A.Dielectric barrier discharge control of a turbulent boundary layer in a supersonic flow[J].Applied Physics Letters,2010,97（4）:1⁃3. [5] ZONG Haohua,KOTSONIS M.Formation,evolution and scaling of plasma synthetic jets[J].Journal of Fluid Mechanics,2018,837:147⁃181. [6] SAMIMY M,KIM J H,KASTNER J,et al.Active control of high⁃speed and high⁃Reynolds⁃number jets using plasma actuators[J].Journal of Fluid Mechanics,2007,578:305⁃330. [7] KIM J H,NISHIHARA M,ADAMOVICH I V,et al.Development of localized arc filament RF plasma actuators for high⁃speed and high Reynolds number flow control[J].Experiments in Fluids,2010,49（2）:497⁃511. [8] NISHIHARA M,TAKASHIMA K,RICH J W,et al.Mach 5 bow shock control by a nanosecond pulse surface dielectric barrier discharge[J].Physics of Fluids,2011,23（6）:101⁃105. [9] DUCHMANN A,SIMON B,TROPEA C,et al.Dielectric barrier discharge plasma actuators for in⁃flight transition delay[J].AIAA Journal,2014,52（2）：358⁃367. [10] NARAYANASWAMY V,RAJA L L,CLEMENS N T.Control of unsteadiness of a shock wave/turbulent boundary layer interaction by using a pulsed⁃plasma⁃jet actuator[J].Physics of Fluids,2012,24（7）:076101⁃076122. [11] BABINSKY H.Shock wave boundary layer interactions[M].New York:Cambridge University Press,2011:5⁃6. [12] YU W,YI SHIHE,HE L,et al.Experimental studies on flow visualization and velocity field of compression ramp with different incoming boundary layers[J].Chinese Physics B,2014,23（11）:384⁃395. [13] YU W,YI SHIHE,ZHI C,et al.Experimental investigation on structures of supersonic laminar/turbulent flow over a compression ramp[J].Acta Physica Sinica,2013，62（18）:116‑121. [14] DOLLING D S,MURPHY M T.Unsteadiness of the separation shock wave structure in a supersonic compression ramp flow field[J].AIAA Journal,1983,21（12）:1682⁃1634. [15] STEPHAN P,MARTIN M P.Low⁃frequency unsteadiness in shock wave⁃boundary layer interaction[J].Journal of Fluid Mechanics,2012,699:1⁃49. [16] SUN Q,LI Y,CHENG B,et al.The characteristics of surface arc plasma and its control effect on supersonic flow[J].Physics Letters A,2014,378（36）:2672⁃2682. [17] LEONOV S B,YARANTSEV D.Near⁃surface electrical discharge in supersonic airflow:properties and flow control[J].Journal of Propulsion & Power,2012,24（6）:1168⁃1181. [18] WANG J,LI Y H,CHENG B Q,et al.The mechanism investigation on shock wave controlled by plasma aerodynamic actuation[J].Acta Physica Sinica,2009,58（8）:5513‑5519. [19] YAN H,LIU F,XU J,et al.Study of oblique shock wave control by surface arc discharge plasma[J].AIAA Journal,2017,56（8）:1⁃10. [20] GAN T,JIN D,GUO S,et al.Influence of ambient pressure on the performance of an arc discharge plasma actuator[J].Contributions to Plasma Physics,2018,58（4）:260⁃268. [21] TANG Mengxiao,WU Yun,GUO Shangguang,et al.Effect of the streamwise pulsed arc discharge array on shock wave/boundary layer interaction control[J].Physics of fluids,2020,32（7）:076101⁃076114. [22] TANG M X,YUN W,WANG H Y,et al.Characterization of transverse plasma jet and its effects on ramp induced separation[J].Experimental Thermal and Fluid Science,2018,99:584⁃594. [23] 吴云,李应红.等离子体流动控制研究进展与展望［J］.航空学报，2015,36（2）:381⁃405.WU Yun，LI Yinghong.Progress and outlook of plasma flow control[J].Acta Aeronautica et Astronautica Sinica,2015,36（2）:381⁃405.（in Chinese） [24] ZHANG Zhibo,WU Yun,JIA Min,et al.The multichannel discharge plasma synthetic jet actuator[J].Sensors and Actuators A:Physical,2017,253:112⁃117. [25] GAN T,WU Y,SUN Z Z,et al.Shock wave boundary layer interaction controlled by surface arc plasma actuators[J].Physics of fluids,2018,30（5）:055107⁃055121. [26] CAI C P.Energy deposition/absorption effects on a planar shock wave[J].Journal of Thermopyhsics and Heat Transfer,2007,21（1）:252⁃254. [27] TANG M X,WU Y,ZONG H H,et al.Experimental investigation of supersonic boundary⁃layer tripping with a spanwise pulsed spark discharge array[J].Journal of Fluid Mechanics,2022,931（16）:1‑11. [28] ZONG H,KOTSONIS M.Realisation of plasma synthetic jet array with a novel sequential discharge[J].Sensors and Actuators A,2017,266:314⁃317. [29] ZHANG Z,WU Y,SUN Z,et al.Experimental research on multichannel discharge circuit and multi⁃electrode plasma synthetic jet actuator[J].Journal of Physics D:Applied Physics,2017,50（16）:165205⁃165215. [30] 甘甜.脉冲电弧放电等离子体激励器控制激波/附面层干扰不稳定性实验研究[D].西安：空军工程大学，2018.GAN Tian.Experimental investigation of shock wave/boundary layer interaction unsteadiness control by using pulsed arc discharge plasma actuator[D].Xi'an:Air Force Engineering University,2018.（in Chinese） [31] KELKAR S S,GRIGSBY L L,LANGSNER J.An extension of Parseval's Theorem and its use in calculating transient energy in the frequency domain[J].Industrial Electronics IEEE Transactions on,1983,IE⁃30（1）:42⁃45. -
下载:
点击查看大图
计量
- 文章访问数: 67
- HTML浏览量: 26
- PDF量: 39
- 被引次数: 0