摘要
基于二维轴对称N-S方程,利用一阶迎风格式和k-ε湍流模型,对超声速轴对称外压式单/双锥进气道流场进行了数值模拟,所得流场结构清晰。研究结果表明:在设计马赫数为2.5时,对于长度相等且具有同等扩压特性的进气道而言,双锥进气道的总压恢复系数比单锥进气道高,且其稳定工作范围更宽,然而,其出口马赫数比单锥进气道高。在超临界状态下,随着进气道出口反压的提高,结尾正激波向喉道方向移动,结尾激波损失减小,总压恢复系数提高,进气道出口流场畸变程度降低。
Based on the 2D -axisymmetric N -S equations, the first order upwind scheme and k - ε turbulent model are used. The characteristics of flow field in supersonic axisymmetric external - compression inlets are numerically simulated and the flow structures are clearly obtained. Results indicate ： when the design Mach number is 2.5, for the inlets which have the equal length and the same diffuse - compression characteristics, the total pressure recovery coefficient of double - cone inlet is higher than that of single - cone inlet, and its stable operation range is wider than that of single - cone inlet, however, its outlet Mach number is higher than that of single - cone inlet. Under the supercritical operation condition, the increase of backpressure at the exit of the inlet induces terminal normal shock wave to move towards the throat, as a result, the intensity of terminal shock wave weakens, the total pressure recovery coefficient at the exit of the inlet increases, and the distortion degree in flow field at the exit of the inlet drops.
出处
《计算机仿真》
CSCD
北大核心
2009年第5期68-71,共4页
Computer Simulation
