An experimental test campaign was conducted for a rotating detonation rocket engine (RDRE) using gaseous oxygen and RP-2 at operating pressures of 3–18 atm. The copper chamber outer wall was instrumented with embedded thermocouples to provide insight into heat-flux levels for various locations in the chamber at numerous operating conditions and wave topologies. Results were compared to throat-level heat fluxes assuming conventional constant-pressure combustion using existing correlations found by Bartz. These comparisons show that average heat loads in the RDRE are near the estimated constant-pressure throat-level heat fluxes assuming frozen flow chemistry, but substantially lower than predictions with equilibrium chemistry. Heat fluxes in the detonation wave region appeared to be relatively higher than in the product region downstream of the detonation waves. Generally, the measured heat fluxes fell within a range manageable with conventional cooling methods.

针对使用气体氧气和RP-2的旋转爆炸火箭发动机（RDRE）在3–18 atm的工作压力下进行了实验测试。铜制腔室的外壁装有嵌入式热电偶，可以洞悉在多种工作条件和波型拓扑下腔室内各个位置的热通量水平。使用巴茨发现的现有相关性，将结果与假设常规恒压燃烧的喉道热通量进行比较。这些比较表明，假设采用冷冻流化学法，RDRE中的平均热负荷接近估计的恒定压力喉咙级热通量，但远低于平衡化学法的预测值。爆炸波区域中的热通量似乎比爆炸波下游的产品区域中的热通量相​​对较高。通常，测得的热通量落在常规冷却方法可控制的范围内。