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朗曼散射测量法应用于燃烧室和喷管出口附近平面，应用在以氢气／氧气为推进剂的推进器二个试验模型中。测得推进器喷嘴出口燃烧室内的温度、氧气成分和水成分数据。这些数据说明在膜冷却之前喷嘴部分发生不完全燃烧，有强的层形喷嘴温度和成分曲线。应用测得的喷嘴数据作为轴对称Ｎａｖｉｅｒ－Ｓｔｏｃｋｅｓ程序的输入数据和完全应用模块预测喷嘴出口曲线并没有改善整体性能数据。在两种情况下，预测性能都有误差；另外，在安装有相同喷嘴的另一种推进器低面积比喷管出口平面获取温度和氧气密度数据。应用两套输入状态分析预测和测得数据，结果有很大不同。用轴对称程序预测，包括充分混合增加流动的总体性能预测模块，流动都为层流，所以喷嘴部分和燃烧室的三维模式都需要更精确的预测推进器的整体性能。
Longman scattering measurements are applied to the vicinity of the combustor and nozzle exit and are used in two pilot models of a propellant with hydrogen / oxygen. Measured propeller nozzle exit combustion chamber temperature, oxygen composition and water composition data. These data show incomplete combustion of the nozzle section prior to film cooling, with strong nozzle temperature and composition curves. Applying the measured nozzle data as input data to an axisymmetric Navier-Stockes program and applying the module to predict nozzle exit profiles does not improve the overall performance data. In both cases, there is an error in predictive performance; in addition, the temperature and oxygen density data is acquired on a lower area than the nozzle exit plane of another propeller fitted with the same nozzle. Applying two sets of inputs to the state-of-the-art predictions and measured data, the results are quite different. Predicted with an axisymmetric program, including a fully mixed flow-increasing overall performance prediction module, the flow is laminar, so both the nozzle section and the combustor’s 3D model need to predict the overall performance of the thruster more accurately.