马赫数对侧压式高超音速进气道及等直隔离段三维内流场的影响的数值分析

Numerical Study of Mach Number at the 3-D Sidewall Compression Hypersonic Inlet and Isolator

用 N-S方程和 RNG k-ε紊流模型计算了 RBCC用侧压式高超音速进气道三维内流场 ,重点分析了马赫数对流场的影响。从出口截面上气流参数的均匀程度来看 ,Ma3 时比 Ma6时的更均匀 ;从压缩气流的主要部位来看 ,Ma6情况下在支板前肩点之后到喉部截面之前的这个等宽度收敛通道内 ,而 Ma3 时主要是在前肩点之前的收敛通道内 ;从对气流的压缩程度来看 ,Ma6比 Ma3 更大 ;从唇口激波的强度来看 ,Ma6比 Ma3 更强 ;从进气道的流量捕获率来看 ,Ma6比 Ma3 更高 ;高超音速进气道内靠近侧壁以及侧壁和顶板的角区附近是最有可能出现亚音速的区域。

The 3-D inner flow field of sidewall compression hypersonic inlet and the isolator is numerically studied by solving the 3-D Navier-Stokes equation. The RNG κ-ε model is used to solve the turbulence problem. And the analysis is mainly focused on the effect of the Mach number on the flow field. The static pressure distributions along the several special lines and the static pressure, Mach number contours on the characteristic surfaces are presented. According to the homogeneity of the air parameter on the outflow section, it is more homogeneous for Ma=3 than for Ma=6. And the most air is compressed in the iso-wide contract tunnel between the front shoulder of the strut and the throat section of the inlet for Ma=6, while for Ma=3 the air is mainly compressed in the contract tunnel before the front shoulder of the strut. And the air is much more compressed for Ma=6 than for Ma=3. According to the cowl shock wave, it is stronger for Ma=6 than for Ma=3. And the inlet captured mass flow rate is greater for Ma=6 than Ma=3. It is shown that the area near the sidewall and the corner zone between the sidewall and the top wall are the most probable subsonic zones.