摘要
高超声速飞行器目前已经成为世界各大国航空航天发展的主要目标之一。以美国X-43A和X-51两高超声速飞行器为研究对象,对两类飞行器气动性能进行了数值模拟,并以此为基础对比分析了两类高超声速飞行器的一体化气动特性。研究结果表明:燃料入射角对飞行器的稳定性(包括俯仰力矩、滚转力矩)和气动力影响剧烈,在相同的燃料入口条件下(流量、进口压力),入射角-20°可以达到升力最大、俯仰力矩最小状态;在相同的有效容积下,X-51在气动稳定性上明显劣于X-43A,俯仰力矩上高出X-43A15%～28%,滚转力矩上高出10%～24%。
Hypersonic vehicle has become one of main goals about development of aerospace in the major world powers.Analysis research of X-43A and X-51 is conducted.Aerodynamics research of two hypersonic configurations integrated with scramjet is present based on three-dimensional simulation.Investigation shows that fuel impingement angle is of an important influence on moments（including the pitching moment and roll moment） and aerodynamic force.In the same fuel inlet condition,hypersonic vehicle can get the maximum lift and minimum pitching moment in the condition that the fuel impingement angle is-20°.In the same volumetric capacity condition,X-43A has dominant species in aerodynamic stability compared with X-51.The pitching moment and roll moment of X-51 are higher by 15%～28% and 10%～24%,respectively.
出处
《航空工程进展》
2011年第3期305-311,共7页
Advances in Aeronautical Science and Engineering
关键词
高超声速
一体化
气动性能
燃烧室
稳定性
hypersonic
integration
aerodynamics performance
combustion chamber
stability
