提高大迎角跨声速风洞实验堵塞度的有效途径——采用低超声速喷管  

THE METHOD FOR EXTENDING THE RANGE OF ATTACK ANGLE AND BLOCKAGE IN TRANSONIC WIND TUNNEL TESTING-USING LOW SUPERSONIC NOZZLE IN STEAD OF SONIC NOZZLE

作　　者：周长海[1] 

机构地区：[1]沈阳空气动力研究所

出　　处：《空气动力学学报》1990年第4期464-467,共4页Acta Aerodynamica Sinica

摘　　要：本文介绍用低超声速喷管代替声速喷管,解决了大迎角大堵塞度跨声速实验时的风洞壅塞问题。低超声速喷管可以在大堵塞的实验条件下,形成稳定的低超声速流场,消除风洞在大堵塞度实验时的马赫数空白区,从而使风洞的允许实验迎角和堵塞度范围增加一倍,并且能确保流场达到使用指标。模型实验结果和同一尺寸的模型在口径大一倍风洞中实验结果基本重合。Instead of the sonic nozzle, low supersonic nozzles have been utilized to solve the choking problem in transonic wind tunnel testing of high angle-of-attack and high blockage. The low supersonic nozzles can produce steady low supersonic flow field with satisfied quality, double the allowable angles of attack and blockage limits and fill in the gaps in Mach number-attack angle range. The model testing results of small 'wind tunnel are in good agreement with the data obtained in large wind tunnel for this model of same scale.

关 键 词：风洞实验 大迎角 跨声速 喷管 风洞 

分 类 号：V211.753[航空宇航科学与技术—航空宇航推进理论与工程]