当前位置: X-MOL 学术Cryogenics › 论文详情
Our official English website, www.x-mol.net, welcomes your feedback! (Note: you will need to create a separate account there.)
Numerical investigation of nitrogen condensation flow over airfoil in cryogenic wind tunnel
Cryogenics ( IF 2.1 ) Pub Date : 2020-10-01 , DOI: 10.1016/j.cryogenics.2020.103165
Wan Sun , Tao Xu , Yu Hou , Zaiyong Ma , Luteng Zhang

Abstract Cryogenic wind tunnel is an equipment for the requirement of high Reynolds number test of the aircraft via the method of reducing the test temperature. However, the test validity is extremely possible to be destroyed by the occurrence of condensation in cryogenic environment. To understand the characteristics of condensation flow over the airfoil, a two-phase flow was developed with the help of ANSYS Fluent. For 0.137-m NACA 0012-64 airfoil, numerical simulations of 32 cases under three different Reynolds numbers (~26 × 106, ~38 × 106 and ~44 × 106) were implemented. The simulated results show that only when the temperature of local gas-flow crosses the saturation line and is lower than a critical point there is enough condensate to alter some flow properties noticeably, such as pressure, temperature and Mach number. The achievement of maximum local supercooled degree decreases with the increase in operating total pressure. For a given test Reynolds number, when the static pressure and temperature of the gas is on the lower temperature side of the saturation curve, a reduction of operating pressure and temperature among a reasonable range is also believed to not cause the condensation effect on the aerodynamic test. On the bright side, lower operating pressure will provide the advantages of less liquid nitrogen injection and less drive power of fan. From another point of view, under the premise of ensuring that the gas-flow local temperature is higher than that at Wilson point, the reduction in the operating temperature as much as possible can greatly increase the test Reynolds number. The built two-phase model supplies an approach for investigating the condensation effect on airfoil test in cryogenic wind tunnel, and resulting findings guide the determination of working conditions for airfoil Reynolds number test.

中文翻译:

低温风洞机翼上氮凝结流的数值研究

摘要 低温风洞是一种通过降低试验温度的方法来满足飞机高雷诺数试验要求的设备。但是,极有可能在低温环境中发生冷凝而破坏测试的有效性。为了了解机翼上冷凝流的特性,在 ANSYS Fluent 的帮助下开发了两相流。对于 0.137-m NACA 0012-64 翼型,在三种不同雷诺数(~26 × 106、~38 × 106 和~44 × 106)下对 32 个案例进行了数值模拟。模拟结果表明,只有当局部气流温度越过饱和线并低于临界点时,才有足够的凝析油显着改变一些流动特性,如压力、温度和马赫数。最大局部过冷度的达到随工作总压的增加而降低。对于给定的试验雷诺数,当气体的静压和温度处于饱和曲线的较低温度侧时,操作压力和温度在合理范围内的降低也被认为不会对空气动力学产生冷凝效应。测试。从好的方面来说,较低的工作压力将提供较少的液氮注入和风扇驱动功率较小的优点。从另一个角度来看,在保证气流局部温度高于威尔逊点的前提下,尽可能降低工作温度可以大大提高试验雷诺数。
更新日期:2020-10-01
down
wechat
bug