尾翼楔角对通气超空泡特性影响试验研究

Experimental investigation of the effect of tail wings wedge angle on ventilated supercavity hydrodynamic

摘要:

为优化通气超空泡航行体流体动力布局,通过水洞试验,研究了航行体尾翼对通气超空泡航行体流体动力的影响．细致分析了通气超空泡的生成和发展过程,给出了尾翼、尾翼楔角对通气超空泡航行体流体动力的影响规律．试验结果表明:航行体尾翼增大了通气超空泡航行体阻力系数与升力系数．通气超空泡航行体阻力系数与升力系数分别随自然空化数减小而减小．通气超空泡航行体阻力系数与升力系数随通气率增大先小幅增加后减小．尾翼楔角越大,通气超空泡航行体升力系数越大．

Abstract:

To optimize hydrodynamic layout of ventilated supercavity vehicle, the experiments have been done in a ventilated cavitation tunnel to study the relationship between tail wings and hydrodynamic of ventilated supercavity vehicle. Forming process of ventilated supercavity was recorded and analyzed. The influences of the tail wings and its wedge angle on the hydrodynamic of ventilated supercavity vehicle were obtained. Experimental results show that the tail wings increase drag coefficient and lift coefficient. Drag coefficient and lift coefficient decrease with the decrease of nature cavitation number. When increasing ventilation rate, drag coefficient and lift coefficient first increase a little and then decrease. The smaller drag coefficient and the bigger lift coefficient can be achieved at bigger tail wing wedge angle.