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以某轴对称基准弹为模型,通过数值模拟对其进行了准定常和非定常气动特性研究,探索可变翼飞行器在变展长过程中的非定常气动特性。结果表明:在弹翼连续变展长的过程中,非定常气动特性曲线在对应的准定常气动特性曲线周围形成滞回环,若来流马赫数增大,则滞回环变小。当来流为超声速时,轴对称基准弹飞行迎角和变形周期对其非定常气动特性影响较小,而非定常气动特性并不显著,接近于准定常气动特性,在可变翼飞行器设计过程中可以忽略不计;当来流为亚声速时,展长变化对非定常气动特性有一定的影响,不能忽略。
Taking an axisymmetric reference missile as a model, the quasi-steady and unsteady aerodynamic characteristics are studied by means of numerical simulation, and the unsteady aerodynamic characteristics of the variable-wing aircraft during its development are explored. The results show that the unsteady aerodynamic characteristic curve forms a hysteretic loop around the corresponding quasi-constant aerodynamic characteristic curve during the continuous expansion of the missile wing, and the hysteresis loop becomes smaller if the Mach-number of the incoming flow increases. When the incoming flow is supersonic, the angle of attack and deformation cycle of the axisymmetric reference missile have little effect on the unsteady aerodynamic characteristics, but the unsteady aerodynamic characteristics are not significant and close to the quasi-steady aerodynamic characteristics. In the design process of the variable wing aircraft Can be neglected; when the incoming flow is subsonic, the variation of the span has a certain influence on the unsteady aerodynamic characteristics and can not be neglected.