The big temperature gradient in hypersonic tip wedge structure was calculated and simulated,and key thermal simulation parameters were presented.Since the single spout heating method can not simulate the heat flux density satisfactorily on the rear plate,a dual-mode heating method was developed to solve this problem,covering a high temperature flow with small spout in the center enveloped by a lower temperature flow.A typical hypersonic condition was simulated using CFD method.It shows that this new heating method can accurately simulate the hypersonic heat flux distribution of the tip wedge by effectively meliorating the heat flux distribution on the rear plate and maintaining the high heat flux density on the stagnation zone.The simulation of transient temperature distribution and big temperature gradient in the interior of tip wedge structure also gets very good results to support this strategy.Meanwhile,the dual-mode heating method can not only greatly reduce the spout size and speed of high temperature flow,but also greatly improve the test ability of electric arc wind tunnel to satisfy larger size of tip wedge structure.
董素君,李志杰,王浚.尖楔结构低速高/中温双路气流组合热试验方法[J].航空动力学报,2013,28(2):290~296. DONG Su-jun, LI Zhi-jie, WANG Jun. Combined heating method of low speed and high/middle temperature gas flow for thermal test of tip wedge structure[J]. Journal Of Aerospace Power,2013,28(2):290-296.复制