火箭喷管两相流动性能计算公式

为方便应用两相流动模型对火箭发动机进行性能预示以及提高性能预示精度,利用火箭喷管内的一维两相流动的数值计算数据,通过对火箭喷管一维两相流动参数与纯气相流动变化规律的对比计算与分析,得到火箭喷管在两相流动下的性能(包括质量流量、排气速度和压强比)计算公式.该计算公式考虑了两相流动中所有的因素,如比热比、凝聚相尺寸、凝聚相百分比,甚至喷管尺寸等,具有广泛的适应性.利用这些公式与理论计算结果进行了对比,结果表明其理论预示精度达到千分位至万分位,并使得两相流动模型在火箭发动机中的应用分析得到简化,有利于提高火箭发动机性能的预示精度.

Property Formulae of Rocket Nozzle With One-Dimension Two-Phase Flow

To predict rocket properties by two-phase flow model and to improve prediction precision,the contrastive calculation and analysis on one-dimension pure gaseous flow and one-dimensional two-phase flow in nozzle by their numerical solution were carried out.Based on the model of one-dimension two-phase flow,the properties formulae including mass flow,flow velocity and pressure ratio,were developed contrastively with pure gaseous flow.The formulae may be widely applied as all factors in two-phase flow were considered,such as specific heat ratio,dimension and proportion of condensed phase,dimension of nozzle,etc.The computed results of the formulae show that the formulae have very high prediction precision which can reach permillage,and it can greatly simplify the applicative analysis of two-phase model on rocket motors to improve prediction precision of rocket properties.