Dataset for direct numerical simulations of a transonic airfoil at a Reynolds number of Re=500,000

These three folders comprise datasets corresponding to figure 5, figure 6 and figure 8 in Zauner et al. (2018):M. Zauner, N. De Tullio and N. Sandham,
"Direct numerical simulations of transonic flow around an airfoil at moderate Reynolds numbers." in the AIAA Journal, 2018. https://doi.org/10.2514/1.J057335All simulations were carried out at a Mach number of M=0.7 and a Reynolds number of Re=500,000.Description of content:
- Fig5: Average skin-friction coefficient and pressure coefficient as a function of axial chord position.
- Fig6: Skin friction as a function of time and space for the reference solution (case C0), the simulation with a grid refined in the xy-plane (G1) and the simulation with the reference xy-plane refined in the spanwise direction (G2).
- Fig8: Instantaneous lift coefficient and surface density as function of time. The surface density is recorded at 10%, 30%, 50%, 70% of the axial chord length and at the leading- as well as trailing edge.
- Movie showing vorticity contours in red and blue, and strong pressure gradients in the background.

本数据集包含三个文件夹，分别对应Zauner等人（2018）发表于《AIAA Journal》的研究中的图5、图6与图8：M. Zauner、N. De Tullio及N. Sandham的《跨音速翼型中等雷诺数流动直接数值模拟》（Direct numerical simulations of transonic flow around an airfoil at moderate Reynolds numbers），2018年，DOI：10.2514/1.J057335。
所有模拟均设置马赫数M=0.7，雷诺数Re=500,000。
内容说明如下：
- 图5：轴向弦长位置对应的平均表面摩擦系数与压力系数。
- 图6：参考解（工况C0）、xy平面网格加密模拟（G1）以及参考xy平面沿展向加密的模拟（G2）的表面摩擦系数随时间与空间的分布。
- 图8：瞬时升力系数与表面密度随时间的变化关系。其中表面密度的采样位置分别为轴向弦长的10%、30%、50%、70%处，以及翼型前缘与后缘。
- 附带展示红、蓝两色涡量等值线与背景强压力梯度的动画。