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首页> 外文会议>AIAA SciTech Forum and Exposition >Unsteady Numerical Simulation on Angle-of-Attack Effects of Tractor-Propeller/Wing and Pusher-Propeller/Wing Interactions
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Unsteady Numerical Simulation on Angle-of-Attack Effects of Tractor-Propeller/Wing and Pusher-Propeller/Wing Interactions

机译：拖拉机-螺旋桨/机翼与推进器-螺旋桨/机翼相互作用的攻角效应的非稳态数值模拟

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In order to realize the Mars airplane with high flight performance and sufficient strength, the propeller/wing interaction flow field and its aerodynamic unsteadiness need to be clarified. Thus, in this study, we conducted unsteady numerical simulations on the propeller/wing interaction at Mars-atmospheric low Reynolds number {Re = 3.0X104). The propeller was installed in front of or behind the fixed main wing (called as Fr. Prop, or Rr. Prop, positioning), and these results were compared with the case without the propeller or the fixed wing (called as Wing Only or Prop. Only configuration). According to the results, in Fr. Prop., the lift coefficient of the fixed wing increased linearly against the angle-of-attack because the propeller slipstream favorably suppressed the growth of separation over the fixed wing. Besides, the corresponding thrust coefficient of the propeller was about 20 - 75% larger than Prop. Only. On the other hand, in Rr. Prop., although the thrust coefficient of the propeller was 95-230% larger than Prop. Only, the azimuthal fluctuation of thrust coefficient of the propeller was enormous because the low-velocity boundary layer behind the fixed wing unsteadily interfered with the propeller. These results suggest that the strength design of an airplane flying at low Reynolds numbers must take into account the aerodynamic force fluctuations caused by the propeller/wing interaction.
机译：为了实现具有高飞行性能和足够强度的火星飞机，需要弄清螺旋桨/机翼相互作用的流场及其空气动力学的不稳定性。因此，在这项研究中，我们对火星-大气低雷诺数（Re = 3.0X104）的螺旋桨/机翼相互作用进行了非稳态数值模拟。螺旋桨安装在固定主翼的前面或后面（称为Fr. Prop或Rr。Prop，定位），并将这些结果与没有螺旋桨或固定翼的情况（称为“仅机翼”或“ Prop”）进行比较。 （仅配置）根据结果​​，以神父为准。因此，固定翼的升力系数相对于攻角呈线性增加，这是因为螺旋桨滑流有利地抑制了固定翼上的分离增长。此外，螺旋桨的相应推力系数比仅道具大约大20-75％。另一方面，在Rr。尽管该螺旋桨的推力系数仅比螺旋桨大95-230％，但由于固定翼后面的低速边界层不稳定地干扰了螺旋桨，因此螺旋桨的推力系数的方位角波动很大。这些结果表明，以低雷诺数飞行的飞机的强度设计必须考虑到螺旋桨/机翼相互作用引起的空气动力波动。

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