【摘要】：將納秒脈沖驅(qū)動的介質(zhì)阻擋放電等離子體激勵器應(yīng)用到NASA SC(2)-0712翼型上,在迎角分別為15°和20°時,開展了在不同雷諾數(shù)下的分離流動控制研究。通過模型表面靜壓測量,得到了不同激勵頻率下的分離流動控制效果。對翼型表面壓力進(jìn)行分布積分,得到了在不同雷諾數(shù)和激勵頻率下的升力系數(shù),表明分離流的控制效果有一個較寬的激勵頻率范圍,只要激勵頻率落在相應(yīng)的頻帶范圍內(nèi),均能實現(xiàn)有效的分離抑制。流動顯示結(jié)果表明,分離流的控制在瞬時表現(xiàn)為放電后可形成大尺度旋渦擬序結(jié)構(gòu)。旋渦的周期性產(chǎn)生、運動和演化造成了分離剪切流動的動態(tài)變化過程,從而促進(jìn)了高/低速氣流的動態(tài)摻混。
[Abstract]:The dielectric barrier discharge plasma exciter driven by nanosecond pulse is applied to the NASA SC (_ 2)-0712 airfoil. The separation flow control under different Reynolds numbers is studied at 15 擄and 20 擄of attack respectively. By measuring the static pressure on the surface of the model, the control effect of separated flow at different excitation frequencies is obtained. By integrating the surface pressure of the airfoil, the lift coefficients at different Reynolds numbers and excitation frequencies are obtained. The results show that the control effect of the separation flow has a wide excitation frequency range, as long as the excitation frequency falls within the corresponding frequency band, Can achieve effective separation inhibition. The flow display results show that the control of the separation flow can form a large scale vortex sequence structure after transient discharge. The periodic generation, movement and evolution of the vortex lead to the dynamic variation process of the separated shear flow, thus promoting the dynamic mixing of the high / low velocity flow.
【作者單位】： 南京航空航天大學(xué)航空宇航學(xué)院;
【基金】：國家自然科學(xué)基金(11532007) 中央高�；究蒲袠I(yè)務(wù)費專項資金(NP2014605) 江蘇省研究生培養(yǎng)創(chuàng)新工程(KYLX_0216) 南京航空航天大學(xué)基本科研業(yè)務(wù)費資助項目(NS2013013);南京航空航天大學(xué)研究生創(chuàng)新基地(實驗室)開放基金(kfjj201401)~~
【分類號】：V211

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相關(guān)期刊論文 前8條

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本文編號：2363370