连续式跨声速风洞压力损失计算研究

Research on the calculation of pressure loss in continuous transonic wind tunnel

为满足未来先进航空航天型号的发展需求,我国逐步展开了大型跨声速风洞建设工作;由于过去从未开展过大型连续式跨声速风洞建设,建设经验较为有限。连续式风洞压力损失估算及各部段气动参数计算是风洞结构、测控系统和动力系统设计的输入条件;压力损失估算结果的准确性,直接影响了风洞动力系统设计的难度。本文结合经典的压力损失计算方法,针对损失的关键部位,结合CFD数值模拟及缩比部段试验结果进行全面的分析,给出了特殊部段尤其是试验段的损失系数,并通过多次迭代计算的方式,给出了各部段气动性能。最后,将风洞压力损失估算值与某0.6 m量级连续式跨声速风洞试验结果进行对比,估算偏差在7.5%以内。

In order to meet the demand of the development of advanced aerospace models in the future,the construction of large-scale transonic wind tunnels has been carried out.Since the construction of large-scale continuous transonic wind tunnels has never been carried out in the past,construction experience is limited.The estimation pressure loss of the continuous wind tunnel and the calculation of aerodynamic parameters of various parts are the design input conditions for the wind tunnel structure system,measurement and control system,and power system.The accuracy of pressure loss estimation results directly affects the difficulty of the wind tunnel power system design.Using the classical pressure loss calculation method combined with the CFD numerical simulation,this paper comprehensively analyzes the key parts of the loss and the results of scaled section test,and gives the loss coefficient of the special section,especially that of the test section,more accurately.The iterative calculation method gives the aerodynamic performance of each section accurately.Finally,by comparing the estimated value of the wind tunnel pressure loss with the test results of 0.6 m continuous wind tunnel,the estimated uncertainty is within 7.5%.