摘要
在高速旋转条件下,利用二维轴对称N-S方程对唇缘钝化的超声速弹用进气道内外的复杂流场进行了数值模拟,所得流场结构清晰。湍流模型为RNGk-ε两方程模型,数值格式为一阶迎风格式。获得了在设计马赫数下不同外罩唇缘钝化半径对进气性能参数的影响。研究表明,在唇缘钝化半径合理增大的情况下,进气道的稳定工作范围变宽,总压恢复系数提高,唯一不利因素为进气道总阻力有所增大,证实唇缘钝化后的进气道能满足固冲增程炮弹的使用要求。
Under the high-speed spinning condition, the complex flow field of a supersonic mixed-compression ramjet inlet with blunted-lip cowl was numerically simulated by using the 2D-axisymmetric N-S equations, and the flow structures were clearly obtained. The two-equation RNG κ-ε turbulence model and the first order upwind scheme were used. The influence of different bluntness radius of cowl lips on the performance parameters of the inlet at design Mach number was studied. The reasonable increase of bluntness radius of the cowl lip tends to make the stable operation range of inlet broadened and the total pressure recovery increased, and the only disadvantage is the increase of total drag of inlet. The mixed-compression inlet with blunted-lip cowl is applicable to the solid fuel ramjet assisted range projectile.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2009年第5期514-517,共4页
Journal of Solid Rocket Technology
关键词
钝化唇缘
混压式进气道
高速旋转
数值模拟
blunted-lip cowl
mixed-compression inlet
high-speed spinning
numerical simulation
