折叠舵外翼气动特性研究

采用风洞试验和CFD相结合的方法对机载导弹折叠舵外翼气动特性进行了研究,研究内容包括外翼折叠角、迎角、来流Ma数、气动滚转角等,通过研究推导建立了外翼气动载荷的经验计算公式。研究结果表明,"×"型状态下外翼载荷随外翼展开而变大,在折叠角约30°附近载荷最大。CFD计算与试验数据吻合良好,不同Ma数下气动系数差别较小,Ma=1.2时气动系数值最大。大量计算数据表明,外翼气动载荷与当地气流偏角存在正相关性,并可以写成合成迎角,滚转角、舵面方位角和折叠角的函数。在迎风区预测值与样本值几乎完全重合,而在背风区受弹身干扰而存在一定误差。

Study on aerodynamics of a folding wing

The aerodynamic characteristics of a folding wing of airborne missiles is investigated by wind tunnel experiments and computational fluid dynamics(CFD).The effects of the folding angle,the angle of attack(AoA),the Mach number,the aerodynamic roll angle,etc.are inspected.We establish an empirical formula for the aerodynamic load on the outer wing.The CFD results agreed well with those in experiments.Results indicate that the aerodynamic force on the outer wing is proportional to its folding angleδ,with its maximum obtained aroundδ=30°.The effect of the Mach number is the most evident at Ma=1.2,but it is generally small.Computational results show that the aerodynamic load on the outer wing is positive correlated with the local stream angle,and can be expressed as a function of the AoA,the roll angle,the position angle,and the folding angle.At the windward side,the predicted value agree well with the sample value,while at the leeward side,there were some errors due to the interfere of the missile body.