炮弹固冲增程发动机进气道的风洞实验研究  

Wind tunnel experimental research on the inlet for solid fuel ramjet assisted projectile

作　　者：谭献忠[1] 刘猛 徐琴[1] 

机构地区：[1]南京理工大学能源与动力工程学院,南京210094 [2]海军驻沈阳地区弹药专业军事代表室,沈阳110045

出　　处：《实验流体力学》2013年第2期63-67,共5页Journal of Experiments in Fluid Mechanics

摘　　要：进气道是冲压发动机的重要部件,它的性能关系着炮弹冲压增程发动机性能的好坏。文章阐述衡量炮弹固体燃料冲压增程发动机进气道性能的指标,介绍冲压发动机进气道的分类,着重给出了某炮弹固冲增程发动机混压式双锥进气道在马赫数2.0096时的风洞实验结果,并进行了详细的分析。研究表明,实验马赫数2.0096时,在进气道有效流通面积范围内,随着进气道有效流通面积的减小,总压恢复系数增加;随着弹体迎角的增加,总压恢复系数降低。The inlet is such an important component of ramjet that its performance makes an overall effect on the quality of the solid fuel ramjet assisted projectile. This paper elaborated on the performance index of the inlet for solid fuel ramjet assisted projectile and introduced the clas- sification of the inlet for solid fuel ramjet. The emphasis of this paper is put on the introduction to the provided wind tunnel experimental result of the mixture pressure type bi-cone inlet for solid fuel ramjet of a assisted projectile when Mach number is 2. 0096, and offer detailed analysis of ex- perimental results. When Mach number is 2. 0096, studies have shown that, within the effective range of flow section area, total-pressure recovery coefficient increases with the decrease in terms of flow section area of the inlet. In addition, total-pressure recovery coefficient decreases with in- crease in terms of attack angle of the ramjet assisted projectile.

关 键 词：冲压发动机 进气道 风洞实验 总压恢复系数 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程] V211.48