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本文介绍战术弹纵横向气动特性的计算方法,其中用吸力比拟法计算翼的非线性力,用冲击流比拟法计算体的非线性力。所谓冲击流比拟,就是有攻角旋成体的横向流动沿轴向的发展,与从静止突然开始运动的二维圆柱绕流随时间的发展相似。部件之间的相互干扰将采用干扰因子和当量攻角法计算。给出了导弹上的自由涡轨迹和自由涡产生的翼面上下洗角分布。本方法适用于计算单独弹身、翼-身组合体、身-尾组合体和全弹在亚、超音速范围内的纵横向气动特性,其攻角一般在0°～20°之内,即弹翼上的涡不发生破裂,弹身体涡保持在对称性的攻角范围之内。此外,导弹可以绕其纵轴滚转,弹翼或尾翼呈“+”字形或“×”形。操纵面是全动弹翼或全动尾翼,并可作俯仰、偏航和滚转操纵。不同外形战术弹的计算结果表明,其纵向气动特性与实验值较符合,横向气动特性误差稍大。
This paper introduces the method of calculating the longitudinal and lateral aerodynamic characteristics of a tactical missile. The non-linear force of the wing is calculated by the suction ratio method, and the non-linear force of the body is calculated by the impulse flow analogy method. The so-called impact flow analogy, is the angle of rotation of the body of the lateral flow along the axial development, and suddenly began to move from static two-dimensional cylindrical flow over time similar to the development. Mutual interference between components will be calculated using the interference factor and equivalence angle of attack. The distribution of upper and lower washing angle of the airfoil generated by free vortex trajectory and free vortex is given. The method is suitable for calculating the vertical and horizontal aerodynamic characteristics of single body, wing-body combination, body-tail combination and full bullet in sub-hypersonic range. The angle of attack is generally within 0 ° ~ 20 ° The vortex on the wing does not rupture, and the body vortex remains within the angle of attack of symmetry. In addition, missiles can roll around their longitudinal axes, with the ”+“ or ”x" shape of the wing or tail. The control surface is fully or fully movable tail wing, and for pitch, yaw and roll control. The calculation results of different shape and tactical shells show that their longitudinal aerodynamic characteristics are in good agreement with the experimental values and the lateral aerodynamic characteristics are slightly larger.