数值算例表明本文方法是求解带操纵面偏转的翼身组合体绕流的有效方法。

Numerical results show that present method is an effective one for solving the flow around wing body configuration with control surface deflection.

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数值算例表明该方法是求解带操纵面偏转的翼身组合体绕流的有效方法。

Numerical results show that the present method is effective one for solving the flow around a wing body combination with control surface deflection.

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为了验证方法和程序的正确性，论文中对M6机翼和F4翼身组合体的流场进行了数值模拟，并与试验结果进行了对比。

The viscous flow around M6 wing and F4 wing-body configuration are simulated and compared with the results of wind tunnel experiment.

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