大规模CFD流场可视化分析系统的应用

设计了大规模计算流体动力学（CFD）流场可视化分析系统（FVAS），系统具有完善而实用的大规模三维定常和非定常流场数据预处理与特征提取、体绘制、几何图形（流线、等值面等）绘制、纹理绘制等功能，并提供多种数据分析手段和良好的交互方法.通过8种展示方式、3种显示模式以及5种视图类型展示流场数据内外流结构特征及其复杂的物理现象.同时系统针对时变数据提供动画展示功能并支持单机多核并行.案例分析表明该系统简单实用，通用性高，多种混合绘制技术能够有效展现燃烧室、进气道等流场数据内部反应情况，切面、剖分等交互方式多视图显示局部细节特征，并通过图表、曲线图等分析工具统计分析具体网格单元的信息.完成测试案例300例，与传统CFD软件相比提升70%以上的绘制效率，系统故障率为0.6%，功能事务成功率100%，有效加速对流场数据的分析统计过程.      

Experimental investigation of expansion effect on shock wave boundary layer interaction near a compression ramp

The experiment is conducted to investigate the effect of expansion on the shock wave boundary layer interaction near a compression ramp. The small-angle expansion with an angle degree of 5° occurs at different positions in front of the compression ramp. The particle image velocimetry and flow visualization technology show the flow structures, velocity field, and velocity fluctuation near the compression ramp. The mean pressure distribution, pressure fluctuation, and power spectral density are measured by high-frequency response pressure transducers. The experimental results indicate that the expansion before the compression ramp position affects the shock wave boundary layer interaction to induce a large-scale separation. But the velocity fluctuation and pressure fluctuation are attenuated near the large-scale flow separation region. When the expansion occurs closer to the compression ramp, the expansion has a more significant impact on the flow. The fluctuation of velocity and pressure is significantly attenuated, and the wall pressure rise of the separation point is reduced obviously. And the characteristic low-frequency spectrum signal related to the unsteadiness of the shock wave boundary layer interaction is significantly suppressed. In addition, variation of the separation region scale at different compression angle degrees is distinctive with the effect of expansion.     

作战效能评估研究的可视化分析

以CNKI数据库为数据源,选取1 200余篇作战效能评估研究领域的文献为对象,采用文献计量与科学知识图谱技术,进行分析和对比,并绘制该领域研究的可视化图谱。通过图谱分析,梳理该研究领域的演进历程,探讨该领域的研究热点和前沿,以提高对该领域的理解和认知,为该领域的研究提供重要参考。     

航空发动机主燃烧室出口温度场可视化设计

为了满足航空发动机主燃烧室试验出口温度场可视化需求,基于主燃烧室出口温度场测试原理,通过温度数据网格化、温度数据-颜色映射、以云图形式显示出口温度场数据的方法进行温度场可视化设计,并在Visual Basic 6.0下基于Tee chart控件开发了出口温度场可视化软件。应用结果表明:在试验中,通过与现有测控软件出口温度场数据交互,可视化软件能够实时、真实、直观地显示主燃烧室出口温度场变化情况,有助于试验人员快速判断出口温度场品质,进而缩短试验时间,降低试验费用,有效提高试验效率。