CAJ | 학술논문

为了研究亚、跨声速底排减阻特性，采用了底排氢加空气燃烧和底排冷空气的方法进行底排减阻特性的风洞实验研究，实验的马赫数范围为M∞=0.71～1.55。从研究结果看出，底排冷空气的减阻率确实很低，但氢加空气燃烧的底排减阻率是很高的，其最大减阻率△Cmax=40％～120％，比冷排气要高一个量级。说明在亚、跨声速下采用底排燃烧的方法仍可有效减少弹丸底部阻力增加射程。
위료연구아、과성속저배감조특성，채용료저배경가공기연소화저배랭공기적방법진행저배감조특성적풍동실험연구，실험적마혁수범위위M∞=0.71～1.55。종연구결과간출，저배랭공기적감조솔학실흔저，단경가공기연소적저배감조솔시흔고적，기최대감조솔△Cmax=40％～120％，비랭배기요고일개량급。설명재아、과성속하채용저배연소적방법잉가유효감소탄환저부조력증가사정。
An investigation of wind tunnel tests of base bleed is conducted, in order to research the characteristics of base drag reduction with base bleed burning H2 + air and base bleed cold air in subsonic and transonic speeds. The Mach numbers are 0.71 ～ 1.55. From results of it, the base drag reduction rate with base bleed cold air is low, but it with base bleed burning H2 + air is much higher than base bleed cold air, that its maximum of base drag reduction rate is 40％～120％. It is shown that reducing the base drag of projectile and increasing the range of it are possible by means of base bleed burning in subsonic and transonic speeds.