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针对所设计的自然层流翼型,在高速风洞中开展了自然层流翼型高雷诺数风洞试验研究。试验运用了测压和红外成像等技术手段,在马赫数Ma=0.74和雷诺数Re=1.5×10~7条件下获得了压力分布、升力系数、阻力系数、俯仰力矩系数和红外图像。试验结果表明,在试验条件下,该翼型上表面能够保持良好的顺压梯度;该翼型具有良好的纵向气动特性;在迎角α=0°时,上、下翼面流动均能保持约60%的层流面积区。
In view of the natural laminar flow airfoil, the natural laminar airfoil with high Reynolds number wind tunnel test is carried out in high speed wind tunnel. The pressure distribution, lift coefficient, drag coefficient, pitch moment coefficient and infrared image were obtained under the conditions of Mach number of Ma = 0.74 and Reynolds number of Re = 1.5 × 10 ~ 7 by means of pressure measurement and infrared imaging. The experimental results show that the upper surface of the airfoil can maintain a good pressure gradient under the test conditions. The airfoil has good longitudinal aerodynamic characteristics. When the angle of attack α = 0 °, the upper and lower surfaces of the airfoil flow can be maintained About 60% of the laminar flow area area.