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通过数值求解三维NS(Navier-Stokes)方程组,对正常式布局战术导弹超声速绕流进行了数值模拟.来流马赫数等于2.0,来流高度20 km.计算中采用三种不同大小的舵面与弹体缝隙,分别为0.005,0.015和0.025倍弹径.得到了不同攻角、不同舵偏状态的舵面气动载荷,主要研究了舵面与弹体间缝隙大小对迎风面与背风面舵面法向力系数及舵面压心位置的影响.数值计算表明,舵面缝隙变化对舵面气动特性影响很小.
The Navier-Stokes equations were numerically solved to simulate the supersonic flow around a normal layout tactical missile with a Mach number of 2.0 and a flow height of 20 km. Three different sizes of rudder surfaces And the gap of the projectile are respectively 0.005, 0.015 and 0.025 times the spring radius.The aerodynamic loads on the rudder surfaces with different angles of attack and deflection are obtained. The effects of the gap between the rudder surface and the projectile on the windward and leeward surfaces Normal force coefficient and the position of the rudder pressure center.The numerical results show that the change of the rudder gap has little effect on the aerodynamic characteristics of the rudder surface.