Development of Low Density Wind Tunnel to Simulate Atmospheric Flight on Mars
Development of Low Density Wind Tunnel to Simulate Atmospheric Flight on Mars
复制标题
DOI：
10.2514/6.2009-1517
复制
发表时间：
2009-01
期刊：
影响因子：
--
通讯作者：
M. Anyoji;H. Nagai;K. Asai
中科院分区：
文献类型：
--
作者：
M. Anyoji;H. Nagai;K. Asai
东北大学设计并建造了一种新型风洞，可以模拟火星大气中的翼型流动。该风洞由引射器驱动，旨在模拟由CO2组成的低密度火星大气。初步的性能测试是使用空气来研究隧道的运行包络线。结果表明，该风洞可覆盖雷诺数10 4 ~ 10 5，马赫数0.71的范围，可模拟火星飞机的低雷诺数、高亚音速流动。还进行了标定试验，以研究试验段的流动特性。可以确认，即使当总压力为1 kPa时，在试验段中流动也保持均匀。边界层发展对沿试验段沿着静压梯度有显著影响。结果表明，这些边界层效应可以通过倾斜试验段的上下壁来校正。
A new type of wind tunnel that can simulate airfoil flow in the Mars atmosphere has been designed and constructed at Tohoku University. This wind tunnel is driven by ejector and designed to simulate low-density Martian atmosphere consisting of CO2. The preliminary performance tests were conducted using air to investigate the operating envelop of the tunnel. It was demonstrated that this wind tunnel could cover the Reynolds number range from 10 4 to 10 5 and the Mach number range up to 0.71, allowing us to simulate low Reynolds number and high subsonic flow on Mars airplanes. Calibration tests were also conducted to investigate the flow characteristics in the test section. It was confirmed that the flow was kept uniform in the test section even when the total pressure was 1 kPa. There were significant effects of the boundary layer development on static pressure gradient along the test section. It was found that these effects of boundary layers could be corrected by inclining both the upper and lower walls of the test section.