The propulsive performance for an H₂/O₂ and H₂/Air rotating detonation engine (RDE) with conic aerospike nozzle has been estimated using three-dimensional numerical simulation with detailed chemical reaction model. The present paper provides the evaluation of the specific impulse (I_sp), pressure gain and the thrust coefficient for different micro-nozzle stagnation pressures and for two configurations of conic aerospike nozzle, open and choked aerospike. The simulations show that regardless of the nozzle, increase the micro-nozzles stagnation pressure increases the mass flow rate, the pre-detonation gases pressure and consequently the post-detonation pressure. This gain of pressure in the combustion chamber leads to a higher pressure thrust through the nozzle, improving the I_sp. It was also found that the choked nozzle increases the chamber time-averaged static pressure by 50–60% compared with the open nozzle, inducing higher performance for the same reason explained before.

使用具有详细化学反应模型的三维数值模拟，估算了带有圆锥形气动尖嘴喷嘴的H ₂ / O ₂和H ₂ /空气旋转爆震发动机（RDE）的推进性能。本文提供了对特定冲量（I _sp），不同的微喷嘴滞止压力以及圆锥形气钉喷嘴的两种配置（开放式和cho塞式气钉）的压力增益和推力系数。模拟表明，不管喷嘴如何，增加微喷嘴的停滞压力都会增加质量流量，爆炸前的气体压力，从而增加爆炸后的压力。燃烧室中的这种压力增加导致通过喷嘴的压力推力更高，从而改善了I _sp。还发现与打开的喷嘴相比，节流的喷嘴将腔室的平均时空压力提高了50-60％，从而产生了更高的性能，原因与之前解释的相同。