典型二元高超声速进气道与侧压式进气道的性能比较

Performance comparison between 2-D scramjet inlet and 3-D sidewall compression scramjet inlet

在相同的约束条件下运用高超声速进气道已有的相关设计方法设计了两类典型的二元进气道与侧压式进气道,利用数值模拟手段对两类进气道的流场结构和总体性能开展了对比研究.研究发现,二元进气道出口流场畸变较小,流场均匀性优于侧压式进气道;二元进气道流量系数对飞行马赫数的敏感程度远高于侧压式进气道;设计点,二元进气道性能优于侧压式进气道.非设计点,尤其在接力状态下,侧压式进气道性能突出;侧压式进气道阻力特性优于二元进气道,而二元进气道的前体升力则高于侧压式进气道.

Under the same constraints, a conventional 2-D scramjet inlet and a 3-D sidewall compression scramjet inlet were designed by using the recently developed advanced methodology. The flow field structure and overall performance were studied comparatively and numerically at Ma=4, 5, 6. The results indicate that, the flow field distortion of 2-D scramjet inlet was much weaker than that of the sidewall compression scramjet inlet. The mass capture ratio o{ 2-D hypersonic inlet was more greatly affected by incoming Mach num- bers than that of the sidewall compression inlet. Numerical simulation shows that, the 2-D inlet was superior to the sidewall compression inlet at the design point, while under off-design points, especially at the starting Mach number, the performance of the sidewall compression inlet was obviously superior to the two-dimensional inlet. Under the equivalent compression state, the drag characteristic of the sidewall compression inlet was superior to that of the two-dimensional inlet, while the lift force of the 2-D dimensional inlet was greater than that of the sidewall compression inlet.