二元高超声速变几何进气道气动特性研究

Research on aerodynamic characteristics of 2-D hypersonic inlet

设计了一种唇罩可沿来流方向平移的二元高超声速变几何进气道,对进气道开展了三维数值仿真研究,就气动特性与相应定几何进气道进行了对比.结果表明:通过迎着来流方向平移唇罩,进气道内收缩比由1.80下降至1.57,自起动马赫数由4.9下降至3.4.在来流马赫数为4.0～7.0范围内,变几何进气道与定几何进气道隔离段出口马赫数和增压比相差不大,变几何进气道流量系数和总压恢复系数可实现提升最大值分别为21%和9%.二元高超声速变几何进气道综合气动性能明显高于定几何进气道.

A kind of 2-D hypersonic variable geometry inlet with movable lip along flow direction was designed.Three-dimensional computational fluid dynamics computation was carried out to simulate the flowfield of the inlet.Comparison of the aerodynamics characteristics was made between variable geometry inlet and fixed geometry inlet.Results indicate：by translating lip upstream,the contraction ratio（CR） of the variable geometry inlet decreases from 1.80 to 1.57 and the self-start Mach number decreases from 4.9 to 3.4.Within the Mach number range of 4.0~7.0,no major difference of the isolator exit Mach number and static pressure ratio of both inlets are observed.The mass flow rate and total pressure recovery coefficient of variable geometry inlet are at most 21% and 9% higher respectively compared with fixed geometry inlet.The variable geometry inlet has superior aerodynamic performance.