CAJ | 학술논문

减小冲压增程炮弹特别是进气道的阻力,可以提高炮弹的射程.建立了冲压增程炮弹超音速进气道的物理模型,采用N-S方程,并运用有限体积法对进气道进行了三维流场的数值仿真,得到了超音速进气道的流场结构图及性能参数,有利进行分析.重点研究了攻角对超音速进气道性能的影响.理论计算了进气道的总压恢复系数,并对进气道总压恢复系数的理论计算值与数值模拟值进行比较分析,基本一致.得到的结论为冲压增程炮弹提供了设计有效参考.
감소충압증정포탄특별시진기도적조력,가이제고포탄적사정.건립료충압증정포탄초음속진기도적물리모형,채용N-S방정,병운용유한체적법대진기도진행료삼유류장적수치방진,득도료초음속진기도적류장결구도급성능삼수,유리진행분석.중점연구료공각대초음속진기도성능적영향.이론계산료진기도적총압회복계수,병대진기도총압회복계수적이론계산치여수치모의치진행비교분석,기본일치.득도적결론위충압증정포탄제공료설계유효삼고.
To minimize resistances of ramjet assisted projectile and especially supersonic inlet can improve the fire range of it.Supersonic inlet model of ramjet assisted projectile Was established,by solving Navier-Stokes equations and using finite volume method,numerical Ssimulation of three dimensional flow field for supersonic inlets were numerical simulated,and the contracture of supersonic inlet flow field and performance parameters were obtained and analyzed.Influence of attack angle to supersonic inlet performance was researched.By computing the total pressure recovery coefficient theoretically,the comparative analyses?between theory computation results and numerical simulation results of inlet total pressure recovery coefficient were carried out,and the results were basically accordant.The conclusions provide theoretical references for reducing resistance and extending the fire range of ramjet assisted projectile.