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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ΔCDB max=40%～120%，比冷排气要高—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。
In order to study the drag reduction characteristics of subsonic and transonic bottom row, a wind tunnel experiment was carried out to study the drag reduction characteristics of bottom row hydrogen plus air combustion and bottom row cold air. The Mach number of the experiment was M∞ = 0.71 ~ 1.55. From the results of the study, it can be seen that the drag reduction rate of the bottom row of cool air is really low, but the bottom row drag reduction rate of hydrogen plus air combustion is very high. The maximum drag reduction rate ΔCDB max = 40% ~ 120% Exhaust should be high - an order of magnitude. This shows that in Asian and transonic speeds, the bottom row combustion method can still effectively reduce the resistance at the bottom of the projectile to increase the range.