摘要
为了拓展S形进气道中心线的选择范围,根据S形进气道的几何边界条件,提出一种基于多项式形式的中心线造型方法。依据不同的中心线拐点位置,采用该方法构造九条有代表性的中心线方程,并建立相应的S形进气道的几何造型。通过对不同几何造型进气道的三维N-S方程数值计算,得到S形进气道的总压恢复和DC60等性能指标,并通过分析发现S形进气道中心线拐点位置对这些性能指标的影响。结果表明:随着中心线拐点位置向后移动,总压恢复系数得到提高,但出口不均匀程度变坏。
Based on the geometric boundary conditions of central line of the S-shaped intake, a polynomial con- struction method is put forward in order to extend the selection of central line. Depending on the different posi- tion of inflection point, 9 typical central lines are given, and the respective S-shaped intake geometric models are built up. The total pressure recovery, outlet dynamic pressure and DC6o index are calculated by solving the 3-D Navier-Stokes equations,through anlaysis the relationships between the position of S-shaped intake central line inflection point and the performance parameters are found. The results showed that the total pressure recovery will be improved and the DC60 index will become worse while the inflection point of the central line move from the inlet to the outlet.
出处
《航空工程进展》
2013年第3期376-380,共5页
Advances in Aeronautical Science and Engineering
关键词
S形进气道
中心线方程构造
拐点
S-shaped intake central line equation constructiom inflection point
