航空工程进展
航空工程進展
항공공정진전
ADVANCES IN AERONAUTICAL SCIENCE AND ENGINEERING
2014年
3期
358-363
,共6页
等离子体控制%细长前体%纳秒脉冲激励器%交流高压激励器%大迎角%主动流动控制
等離子體控製%細長前體%納秒脈遲激勵器%交流高壓激勵器%大迎角%主動流動控製
등리자체공제%세장전체%납초맥충격려기%교류고압격려기%대영각%주동류동공제
plasma control%slender forebody%NS-DBD plasma actuator%AC-DBD plasma actuator%high angle of attack%active flow control
为了在更高的风速下实现圆锥前体分离涡的控制,了解AC-DBD和NS-DBD激励器的激励特性,应用交流(AC)放电和纳秒脉冲(NS)放电等离子体激励对20°顶角的圆锥-圆柱组合体圆锥段前体非对称流场进行主动流动控制实验。实验在低速开口风洞中进行,迎角45°,风速5~22 m/s ,流动控制方式为等离子激励器关闭、左舷或右舷等离子体激励器开启三种模式。结果表明:风速5 m/s时,通过AC-DBD的左、右舷激励可控制圆锥前体的非对称流场实现镜像对称,NS-DBD则无明显作用效果;随着风速的提高,AC-DBD对非对称载荷的控制作用逐渐减小,与此同时NS-DBD的控制作用逐渐增加;风速22 m/s时,NS-DBD可实现圆锥前体非对称流场的镜像对称控制,而AC-DBD则无明显作用效果;相对于AC-DBD等离子体激励,NS-DBD对于更高速度下的分离涡流场控制是有效的。
為瞭在更高的風速下實現圓錐前體分離渦的控製,瞭解AC-DBD和NS-DBD激勵器的激勵特性,應用交流(AC)放電和納秒脈遲(NS)放電等離子體激勵對20°頂角的圓錐-圓柱組閤體圓錐段前體非對稱流場進行主動流動控製實驗。實驗在低速開口風洞中進行,迎角45°,風速5~22 m/s ,流動控製方式為等離子激勵器關閉、左舷或右舷等離子體激勵器開啟三種模式。結果錶明:風速5 m/s時,通過AC-DBD的左、右舷激勵可控製圓錐前體的非對稱流場實現鏡像對稱,NS-DBD則無明顯作用效果;隨著風速的提高,AC-DBD對非對稱載荷的控製作用逐漸減小,與此同時NS-DBD的控製作用逐漸增加;風速22 m/s時,NS-DBD可實現圓錐前體非對稱流場的鏡像對稱控製,而AC-DBD則無明顯作用效果;相對于AC-DBD等離子體激勵,NS-DBD對于更高速度下的分離渦流場控製是有效的。
위료재경고적풍속하실현원추전체분리와적공제,료해AC-DBD화NS-DBD격려기적격려특성,응용교류(AC)방전화납초맥충(NS)방전등리자체격려대20°정각적원추-원주조합체원추단전체비대칭류장진행주동류동공제실험。실험재저속개구풍동중진행,영각45°,풍속5~22 m/s ,류동공제방식위등리자격려기관폐、좌현혹우현등리자체격려기개계삼충모식。결과표명:풍속5 m/s시,통과AC-DBD적좌、우현격려가공제원추전체적비대칭류장실현경상대칭,NS-DBD칙무명현작용효과;수착풍속적제고,AC-DBD대비대칭재하적공제작용축점감소,여차동시NS-DBD적공제작용축점증가;풍속22 m/s시,NS-DBD가실현원추전체비대칭류장적경상대칭공제,이AC-DBD칙무명현작용효과;상대우AC-DBD등리자체격려,NS-DBD대우경고속도하적분리와류장공제시유효적。
In order to control the vortex flow over conical forebody under higher wind ,and to understand the characteristic of the AC-DBD and NS-DBD ,alternative current(AC) and nanosecond pulse(NS) plasma dielec-tric barrier discharge(DBD) is applied to the active control of the asymmetrical vortices over the cone of the cone-cylinder .The experiment is performed in a low speed wind tunnel .The angle of attack is 45° and the wind speed ranges from 5 m/s to 22 m/s .Flow control modes of the actuator are plasma off ,port on and starboard on .The result shows that the asymmetrical field can be mirror symmetry control by port on and starboard on of AC-DBD at 5 m/s ,but the NS-DBD is not effective .As the wind speed increased ,the function of the AC-DBD on asymmetric vortices is gradually disappears ,meanwhile the function of NS-DBD is increasing .When the wind speed reaches 22 m/s ,NS-DBD can get the asymmetrical field mirror symmetry ,but the AC-DBD is not effective .This implies that the NS-DBD is more effective to control the separated vortices field at the higher w ind speed relative to the AC-DBD .