An investigation on characteristics of base drag reduction with base bleed in subsonic and transonic speeds

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.