Low Reynolds number airfoil testing in a Mars Wind Tunnel
Low Reynolds number airfoil testing in a Mars Wind Tunnel
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火星风洞中的低雷诺数翼型测试
DOI：
10.2514/6.2010-4627
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发表时间：
2010
期刊：
影响因子：
--
通讯作者：
K. Asai
中科院分区：
文献类型：
--
作者：
M. Anyoji;K. Nose;S. Ida;D. Numata;H. Nagai;K. Asai
在日本东北大学的火星风洞（MWT）上，研究了5%平板和NACA0012-34翼型在低雷诺数（Re=0.43x10 4 ~4.1x10 4）和高亚音速流（M=0.1~0.6）条件下的气动特性。开发了一种双组分平衡系统和压敏涂料（PSP）技术来测量模型上的升力和阻力以及压力分布。对于平板，马赫数效应对其气动性能影响不大，而雷诺数影响升力斜率和阻力特性。相反，对于NACA001234翼型，雷诺数和马赫数效应变得更加突出。在跨临界条件下，升力曲线是高度非线性的，阻力极受层流分离气泡行为的影响。在不同马赫数下得到的结果的比较表明，可压缩性对稳定分离剪切层有作用。该实验验证了MWT可以提供一种独特的能力来研究低雷诺数和高马赫数流动的翼型性能。
The aerodynamic characteristics of a 5% flat plate and NACA0012-34 airfoil in low Reynolds number (Re=0.43x10 4 ~4.1x10 4 ) and high subsonic flow (M=0.1~0.6) were investigated in the Mars Wind Tunnel (MWT) at Tohoku University. A two-component balance system and Pressure-Sensitive Paint (PSP) technique have been developed to measure the lift and drag forces and pressure profiles on the model. For the flat plate, Mach number effect does not have much effect on its aerodynamic performance while Reynolds number affects the lift slope and the drag characteristics. On the contrary, for NACA001234 airfoil, both Reynolds and Mach number effects become more prominent. The lift curves are highly nonlinear and the drag polars are affected by behaviors of a laminar separation bubble in trans-critical condition. A comparison of the results obtained at different Mach numbers has suggested that the compressibility has an effect to stabilize separated shear layer. It has been verified by this experiment that the MWT can offer a unique capability to investigate airfoil performance in low Reynolds number and high Mach number flow.
影响因子：
2.4
作者：
H. Mori;T. Niimi;M. Hirako;H. Uenishi
通讯作者：
H. Mori;T. Niimi;M. Hirako;H. Uenishi