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Numerical and Experimental Determination of Canard Controlled Missile Aerodynamic Coefficients in Subsonic Regime

机译：亚音区中Canard控制导弹空气动力学系数的数值和实验测定

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This paper discusses the computational and experimental approach to the determination of aerodynamic coefficients of canard controlled missile with wrap around tail fin. The paper presents results of subsonic flow at Mach 0.4. Angle of attack of the missile is varied from ?10 to +10 degrees with an increment of 2 degrees. Canard deflection in the pitch plane is also varied at 0, 10, and 15 degrees. The results of the simulation are compared with the experimental data obtained by the wind tunnel measurements. Measured results confirm applicability of Spalart Allmaras turbulence model with adapted computational mesh to the determination of aerodynamic coefficients for canard controlled missiles.
机译：本文讨论了尾翅片包裹套管控制导弹的空气动力系数的计算和实验方法。 本文提出了Mach 0.4的亚音流的结果。 导弹的攻角从？10至+10度随递增2度的变化。 俯仰平面中的Canard偏转也在0,10和15度下变化。 将模拟结果与通过风隧道测量获得的实验数据进行比较。 测量结果证实了Spalart Allmaras湍流模型的适用性，使计算网格适用于Canard控制导弹的空气动力学系数的测定。

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