A numerical investigation of the performance of a supersonic combustor designed for a flight Mach 8 is presented. Numerical simulations are used to assess the characteristics and operational limits of the combustor at design and off-design conditions. The combustor design point corresponds to the cruise condition at a Mach number of 8 and an altitude of 30 km. Off-design conditions correspond to a Mach number of 8 at 28 km altitude and a Mach number of 6 at 26 km altitude. Each off-design condition was investigated at three different angles of attack: 2, 0, and $-2\mathrm{deg}$. For constant flight Mach number and altitude, the variation of the angle of attack showed significant influence on the performance of the combustor, mainly on the ignition length. Flying at a negative angle of attack resulted in intense combustion and reduced ignition length. For the Mach 6 off-design condition, a dual-operation mode (ramjet–scramjet) with regions of subsonic combustion was observed. At such condition, it was possible to extend the operation of the combustor and avoid subsonic combustion regions by varying the angle of attack to a positive value. For a constant flight Mach number and altitude, the variation of the angle of attack showed an interesting mechanism to control combustion.

给出了为8马赫飞行而设计的超音速燃烧器性能的数值研究。数值模拟用于评估燃烧器在设计和非设计条件下的特性和运行极限。燃烧室设计点对应于8马赫数和30 km高度的巡航条件。非设计条件对应于28 km高度的马赫数为8和26 km高度的马赫数为6。在三种不同的攻角下研究了每种非设计条件：2、0和$-2度$。对于恒定的飞行马赫数和高度，迎角的变化对燃烧器的性能有显着影响，主要是在点火长度上。以负迎角飞行会导致强烈燃烧并缩短点火长度。对于6马赫偏离设计状态，观察到具有亚音速燃烧区域的双工模式（冲压喷气发动机-超燃冲压发动机）。在这种情况下，可以通过将迎角改变为正值来扩展燃烧器的运行并避免亚音速燃烧区域。对于恒定的飞行马赫数和高度，迎角的变化显示出一种有趣的控制燃烧的机制。