方案摘要
方案下载应用领域 | 航空航天 |
检测样本 | 航空 |
检测项目 | |
参考标准 | 暂无 |
采用LaVision公司的FlowMaster粒子成像测速系统。测量了超音速气流作用下,机翼表面的流场。研究了火花放电产生局部快速加热对分离点位置的影响。
Experimental investigation of interaction between gas-dynamic perturbations caused
by long spark discharge and separation region on the surface of an aerodynamic model,
streamlined by supersonic airflow with Mach number M=2, is presented in this paper. A
NACA-airfoil with a relative thickness of 12% of the chord length was used as aerodynamic
model. With the help of the Particle Image Velocimetry method airflow was visualized at
various angles of attack, delays 0–100 μs relative to the moment of discharge initiation and at
various values of stored electric energy 0.1–10 J, that was spent for discharge creation. It was found that the flow disturbance caused by the discharge leads to a short-term displacement of separation point downstream.
在一个双稳湍流涡旋火焰中,对间歇性动态的时间-频率定位
Particle-laden Taylor-Couette流:高阶转变和径向局部波浪涡旋的证据
7根杆束的流体-结构相互作用:用实验数据对比数值模拟
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