1) Liquid propulsion engine
液体推进发动机
4) Liquid propellant rocket engine
液体推进剂火箭发动机
1.
The turbulent fluid flow and heat transfer in a regenerative-cooling channel of liquid propellant rocket engine were numerically investigated by solving three-dimensional elliptical Navier-Stokes equations.
应用湍流模型对液体推进剂火箭发动机再生冷却推力室通道的流动与传热进行了三维数值模拟,冷却工质为氢气,其密度、导热系数、动力粘度随着温度和压力而变化,冷却剂比热容及金属固体物性随着温度而变化。
6) liquid rocket engines
液体推进剂火箭发动机
1.
In order to realize the multiple ignitions of liquid rocket engines reliably, gas dynamic resonance ignition was applied to ignite kerosene/oxygen.
为了实现液体推进剂火箭发动机的多次可靠起动 ,将气动谐振点火技术应用于气氧煤油的点火 。
补充资料：航空发动机推重比(见航空发动机推力)
航空发动机推重比(见航空发动机推力)
thrust to weight ratio of aeroengine
hQngkong角dong)1 tuizhongbi航空发动机推重比〔thros*:。wdgh:ra-tio of aeroengine)见航空发动机推力。
说明：补充资料仅用于学习参考，请勿用于其它任何用途。
参考词条