2.4 m连续式跨声速风洞气动设计与研究

Aerodynamic design of 2.4 m continuous transonic wind tunnel

连续式跨声速风洞由轴流压缩机驱动运行,具有运行范围宽、流场品质高、运行时间长等优点,是国际上最主要的跨声速风洞类别。近年来我国飞行器型号研制对大型连续式跨声速风洞的试验需求快速增长,为了弥补我国大型连续式跨声速风洞设备短板,中国航空工业空气动力研究院建设了2.4 m连续式跨声速风洞,该风洞是我国第一座大型连续式跨声速风洞。为了获得最佳的风洞流场品质和气动性能,航空工业气动院研发了多项适用于连续式跨声速风洞的气动外形设计技术,包括风洞的喷管、试验段、二喉道等高速部段的气动设计技术和低速部段气动设计技术。本文详细介绍了连续式跨声速风洞的总体设计要求和主要部段的气动设计方法,并通过CFD计算和风洞试验开展研究与验证。通过应用先进风洞气动设计技术指导风洞建设及调试,2.4 m连续式跨声速风洞的流场均匀性、噪声和湍流度已达到国际先进水平,试验数据品质与国际先进风洞一致。

Driven by axial flow compressor,the continuous transonic wind tunnel has the advantages of wide operating range,high flow field quality and long running time,and is the most important type of transonic wind tunnel in the world.In recent years,the test demand of large continuous transonic wind tunnels for the aircraft development in China is growing rapidly,therefore,the AVIC Aerodynamics Research Institute(AVICARI)built the first continuous transonic wind tunnel of China,i.e.the 2.4 m continuous transonic wind tunnel.In order to obtain the best flow field quality and aerodynamic performance of the wind tunnel,AVICARI has developed a number of aerodynamic design techniques applicable to continuous transonic wind tunnels,including design methods for high-speed sections,such as the nozzle,the test section,the second throat,as well as techniques for the low-speed sections.In this paper,both the overall design requirement and the aerodynamic design methods of some main sections suitable for continuous transonic wind tunnels are introduced in detail,which are studied and verified by CFD and wind tunnel tests.Through the application of these aerodynamic design techniques,the flow field uniformity,noise level and turbulence intensity of the 2.4 m continuous transonic wind tunnel have reached the international advanced level,with the test data in good consistency with those from similar wind tunnels abroad.