The performance (specific impulse, $I_{\mathrm{sp}}$) of a modular, $150\text{-}{\mathrm{lb}}_f$-class rotating detonation rocket engine (RDRE) was measured with three gaseous fuels (methane, ethane, and ethylene) and gaseous oxygen over a wide range of flow rates and equivalence ratios. All tests exhausted to sea level backpressure and were conducted using a calibrated thrust stand and Coriolis mass flow meters. Configurations tested included a straight, open annulus, as well as several converging/diverging annular nozzles. Throughout testing, wave numbers observed via high-speed video varied from 5 to 8 waves, whereas wave speeds varied from 60 to 72% of ideal Chapman–Jouguet velocities. Measured performance ranged from 68 to 85% of ideal liquid rocket engine (deflagration engine) sea-level performance, based on comparisons to ideal NASA Chemical Equilibrium with Applications performance estimates. Additionally, an altitude compensating aerospike nozzle increased performance by 10–13%. Several constricting annular exits were also tested, and yielded increased $I_{\mathrm{sp}}$ with decreasing flow area. Direct detonation upset tests revealed remarkable combustion stability, and extended pulse-mode firings demonstrated the potential for RDREs as attitude control thrusters.

表现（特定冲动， ${\mathrm{一世}}_{\mathrm{SP}}$）， $150\text{--}{磅}_F$使用三种气态燃料（甲烷，乙烷和乙烯）和气态氧，在很宽的流速和当量比范围内测量了一流的旋转爆轰火箭发动机（RDRE）。所有测试均用尽了海平面背压，并使用校准的推力架和科里奥利质量流量计进行。测试的配置包括笔直的，开放的环空以及几个会聚/发散的环形喷嘴。在整个测试中，通过高速视频观察到的波数在5至8波之间变化，而波速在理想Chapman–Jouguet速度的60％至72％之间变化。根据与理想的NASA化学平衡和应用性能估算值的比较，测得的性能范围是理想液体火箭发动机（爆燃发动机）海平面性能的68％到85％。另外，高度补偿气雾喷头的性能提高了10–13％。还测试了几个收缩的环形出口，并提高了产量${\mathrm{一世}}_{\mathrm{SP}}$流动面积减小。直接爆震试验显示了出色的燃烧稳定性，而扩展的脉冲模式点火则证明了RDRE作为姿态控制推进器的潜力。