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正在兴建的2.4m风洞是一座增压回流引射式跨声速风洞。试验段截面尺寸2.4m×2.4m，M＝0．5（0．3）～1．2，1．4（1．8），工作压力最高可达4．5×105Pa。风洞由多喷嘴中压气体引射器驱动。稳定段工作压力由位于风洞主排气系统中的四个主排气阀控制。气流M数分别由栅指或驻室抽气系统控制。精度可达△M=0.002。吹风耗气量仅为相同尺寸的下吹式风洞的1／4。该风洞是发展我国载人飞船、新型歼击机及大型运输机等航空航天飞行器必不可少的重要配套试验设备。本文对风洞总体性能及技术方案的构思和风洞设计特点等方面内容作概要论述。
The 2.4m wind tunnel under construction is a turbocharged recirculation-induced transonic wind tunnel. Experimental section section size 2.4m × 2.4m, M = 0.5 (0.3) ~ 1.2,1.4 (1.8), working pressure up to 4.5 × 105Pa. The wind tunnel is driven by a multi-nozzle medium pressure gas ejector. Stable section operating pressure is controlled by the four main exhaust valves located in the main exhaust system of the wind tunnel. Gas flow M number by the grid finger or chamber exhaust system control. Accuracy up to △ M = 0.002. Air consumption is only the same size of the blow-down wind tunnel 1/4. The wind tunnel is an important ancillary test equipment for developing aerospace vehicles such as manned spacecraft, new fighters and large transport aircraft in China. This paper summarizes the overall performance of the wind tunnel, the concept of the technical scheme and the design features of the wind tunnel.