Simulation of the effect of propeller slipstream on blowing control of flap
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摘要:
采用数值模拟方法,对内吹式附面层控制方案(吹气襟翼)的全机带螺旋桨滑流影响的气动力特性进行仿真计算,并与风洞试验结果对比。将4个螺旋桨区域单独划分网格,在各个域之间通过面搭接网格进行数据传递。采用基于多重参考坐标系的准定常方法和螺旋桨真实旋转的非定常方法,对升阻特性进行计算,并与风洞试验结果进行了对比。结果表明:准定常方法可以大致捕捉到升力特性曲线的发展趋势,但所计算的固定迎角下的升力系数具体数值与试验测试结果存在较大差距,该方法所捕捉的失速迎角也普遍小于试验测试结果,阻力特性也差距较大;非定常方法可以比较准确地捕捉到升力特性曲线发展趋势,对失速迎角及固定迎角下的升力系数具体数值捕捉也比较准确,阻力平均误差控制在15%以内。
Abstract:Numerical simulation method was used to simulate the aerodynamic characteristics of the entire aircraft with propeller slip flow in the internally blown boundary layer control scheme (inflation flaps), and compare them with the wind tunnel test results. The four propeller regions were divided into meshes separately, and data were transferred between each domain through surface overlapping mesh. Using the quasi-steady method based on multiple reference coordinate systems and the unsteady method of real rotation of the propeller, the lift-drag characteristics were calculated and compared with the wind tunnel test results. The results showed that the quasi-steady method can roughly capture the development trend of the lift characteristic curve, but the calculated specific value of the lift coefficient at a fixed angle of attack was far from the wind tunnel test results, and the stall angle of attack captured by this method was generally smaller than the test results, showing a large gap in resistance characteristics; the unsteady method can more accurately capture the development trend of the lift characteristic curve, and the specific value of the lift coefficient under the stall angle of attack and the fixed angle of attack was also more accurate, and the average drag error was controlled within 15%.
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Key words:
- blowing control of flap /
- propeller slipstream /
- slip mesh /
- CFD method /
- wind tunnel test
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