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首页> 外文期刊>Proceedings of the Institution of Mechanical Engineers, Part D. Journal of Automobile Engineering >The impact of inlet flow conditions on the aerodynamic performance of an NACA submerged intake for ground vehicle applications
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The impact of inlet flow conditions on the aerodynamic performance of an NACA submerged intake for ground vehicle applications

机译：进气流量条件对地面车辆应用NACA水下进气口空气动力学性能的影响

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摘要

Results are presented following a series of experimental measurements on a submerged NACA-type intake oriented between -30° and + 30° yaw to the free stream in an atmospheric boundary layer wind tunnel at a unit Reynolds number of nominally 1 × 10~6. The intake was subjected to a range of upstream wall boundary layer conditions, and the mass flow into the intake (as measured by an orifice plate) was monitored to assess the aerodynamic performance. The mass flow data are supported by qualitative flow visualisation within the duct, using a smoke filament illuminated in a laser light sheet in order to gain insight into the flow physics. The intake performance, expressed in terms of a non-dimensional flow momentum coefficient, is seen to degrade both with increasing intake orientation to the free stream (changes of nominally 40% are seen for the angle range tested) and with increasing upstream boundary layer displacement thickness (changes of nominally 30% are seen for the range tested). These data are presented as a graphical carpet plot; it is intended that this is used as a guide to performance prediction in non-aeronautical applications where there are often significant changes in both the local flow direction and the boundary layer thickness. Flow visualisation studies show that the degradation in the intake performance with increasing yaw angle can be attributed to a progressive change in the vortex-pair structure within the intake as the local flow angle is increased. Both an increase in the lateral separation and an increase in the size of the respective vortex cores are considered to act so as to reduce the magnitude of the induced inflow into the intake.
机译：在以名义雷诺数名义上为1×10〜6的单位的大气边界层风洞中，在相对于自由流在-30°至+ 30°偏航角范围内的淹没式NACA型进气口进行一系列实验测量之后，给出了结果。进气口要承受一定范围的上游壁边界层条件，并监视进气口的质量流量（由孔板测量）以评估空气动力性能。质量流量数据由管道内的定性流动可视化支持，使用在激光灯板上照亮的烟丝来深入了解流动物理。进气性能以无量纲流动动量系数表示，随着进气自由流方向的增加（测试角度范围内名义上的变化为40％）和上游边界层位移的增大而降低。厚度（在测试范围内标称变化为30％）。这些数据以地毯状图形表示。旨在将其用作非航空应用中性能预测的指南，在非航空应用中，局部流动方向和边界层厚度通常都发生显着变化。流动可视化研究表明，随着偏航角的增加，进气性能的下降可归因于进气流中涡流对结构随着局部流动角的增加而逐渐变化。侧向间隔的增加和各个涡流芯的大小的增加都被认为是起作用的，以便减小所引起的流入进气口的流入量。

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