【摘要】 采用等激波角设计方法并考虑温度、激波与附面层干扰等的影响 ,对超音速燃烧冲压发动机的二维混压式高超音速前体 /进气道和隔离段的设计进行了探索 ,给出了前体 /进气道和隔离段的几何结构和尺寸。运用二维 CFD数值计算手段 ,对所设计进气道结构进行了修正 ,并计算了设计状态和非设计状态性能和流场。研究表明 ,文中所设计的进气道结构简单、附加阻力较小、总压恢复系数较高 ,所给出的设计方法对于前体 /进气道和隔离段的初步设计具有较好的适用性更多还原

【Abstract】 Aerospace application of scramjet has come to attract more and more attention during the past ten years or so. One area of interest is the proper design of hypersonic forebody/inlet and isolator of integrated scramjet. Even this small area involves rather complicated problems such as starting of the inlet and real air that is rarefied and hot. We have been exploring in the area for the last three years and this paper is a kind of progress report. Subsection 1.1 explains that we design hypersonic forebody/inlet and isolator of integrated scramjet for M =7 and flight attitude H =25 km. Subsections 1.2 and 1.3 present our aerodynamic design of hypersonic forebody/inlet of integrated scramjet; they use constant shock angle method with due consideration for the effect of temperature and shock boundary layer interaction; they describe how to determine the geometry of hypersonic forebody/inlet and check the contraction ratio of inlet with an empirical formula. Section 2 presents our preliminary aerodynamic design method of isolator and derives a semi empirical formula for computing the ratio of length to height of the isolator section. Fig.1 and Table 1 give the configuration and specific values of the dimensions of the designed forebody/inlet and isolator. Section 3 presents performance parameters and flowfield results for given design and off design conditions, which are along the trajectory of constant dynamic pressure. Figs. 4,5,and 6 give calculated results for three performance parameters: mass flow coefficient (Fig.4); additional drag coefficient(Fig.5); total pressure recovery coefficient(Fig.6). Figs. 2,3,7, and 8 give 2D CFD(computational fluid dynamics) results at given design and off design conditions. Numerical results indicate that the forebody/inlet and isolator designed by us are of simple configuration but they can give higher compression ratio, higher total pressure recovery coefficient and lower additional drag.更多还原