【摘要】 采用风洞实验方法 ,研究头部火箭喷流对弹丸气动性能的影响 .实验马赫数为2 ,攻角α =0°～ 6° ,喷咀倾角θ=30° ,喷流压力比 poj/ p∞ =0 ～ 10 2 6 ,喷流介质为冷空气 ,实验结果表明 ,随着 poj/ p∞ 增加 ,弹丸前体阻力系数CF 下降 ,升力系数CY 上升 ,压心 XCP 明显后移 ,头部喷流对弹丸静态气动特性产生有利影响更多还原

【Abstract】 This paper studies influence of rocket jet from the nose on aerodynamics of projectile by means of wind tunnel test. Experimental Mach number is 2, the angles of attack are form 0° to 6°. Jet pressure ratios p oj /p ∞ are 0～102 6. Inclined angle of jets is 30°. The medium of jet is cool air. Experimental results show that the C XF goes down, C Y goes up and CP moves downstream markedly, when p oj /p ∞ increases. The influences of jet from nose are beneficial to static aerodynamics of projectile.更多还原