| 跨声速翼型激波／边界层干扰被动控制的数值模拟计算 |
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| 引用本文： | 王一兵 陈炳永. 跨声速翼型激波／边界层干扰被动控制的数值模拟计算[J]. 空气动力学学报, 1992, 10(2): 185-194 |
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| 作者姓名： | 王一兵 陈炳永 |
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| 作者单位： | 中国科学院力学研究所，北京航空航天大学，北京航空航天大学 北京 100080，北京 100083，北京 100083 |
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| 摘 要： | 本文应用数值计算的方法着重研究了跨声速翼型开孔壁的减阻效果。计算采用了边界层与位流相互作用的模型,藉以了解开孔壁对激波强度及结构的影响和对边界层控制的效果。通过对NACA0012翼型的计算表明,本文采用的自然吹吸的开孔模型能够显著地削弱激波的强度,改善激波的结构,但会使粘性损失增加。在马赫数较小时,翼型开孔后总阻力会增加,而在大马赫数时,开孔翼型的减阻效果才表现出来。这种趋势是与实验结果相吻合的。
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| 关 键 词： | 跨声速 翼型 开孔壁 空穴流动 |
Numerical Simulation of Passive Control of Shock-boundary Layer Interaction for Transonic Airfoil |
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| Wang Yibin Chen Bingyong Zhu Ziqiang. Numerical Simulation of Passive Control of Shock-boundary Layer Interaction for Transonic Airfoil[J]. Acta Aerodynamica Sinica, 1992, 10(2): 185-194 |
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| Authors: | Wang Yibin Chen Bingyong Zhu Ziqiang |
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| Abstract: | The effect of reducing total drag of transonic airfoils is specially studied. An interactive boundary layer (IBL) algorithm is employed in order to observe the influences of porous surface on strength and structure of shocks as well as the effects on controlling the boundary layer. The numerical results of NACA0012 airfoil indicate that the nature blowing-suction porous model can appreciably reduce strength of shock and change its structure, but it can also increase the losses of viscousity. The total drag is increased at lower Mach numbers and reduced at higher Mach numbers. This tendency accords with experimental results. |
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| Keywords: | transonic airfoils shock porous wall porous flow. |
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