冲压空气涡轮流场数值研究主要目的是模拟在实际高空加油工作状态下涡轮变桨距气动特性。
The aim of numerical experiment of ram air turbines is mainly to simulating its adjustable pitch aerodynamic characteristic on the actual flight refuel conditions.
从而为生物质成型燃料燃烧设备热性能、空气动力场、结渣特性、主要设计参数确定等试验奠定了基础。
This will lay the foundation for the thermal performance test, air dynamic field test, dreg characteristic test and determinative test of the main design parameters.
翼型伞空气动力特性研究是研制高性能翼型伞的一个重要内容，而风洞试验是翼型伞气动性能研究的主要手段之一。
One of the main works to development ram air parawing with high performance is to research its aerodynamic characteristics, and the wind tunnel test technique is usually been taken.
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