组合式宽马赫数风洞设计与流场特性

Design and Flow Field Characteristics of a Combined Wide Mach Number Wind Tunnel

脉冲型风洞是开展高超声速飞行器研制和气动热力学研究的重要试验设备。本文基于激波风洞和Ludwieg管风洞组合运行原理,突破了高温管外静态加热技术、高温高压气体隔离技术、大口径高温膜片设计技术等系列关键技术,设计建设了FL-63脉冲型组合式宽马赫数风洞,设计马赫数范围3.0~10.0,采用双模式组合运行模式,中低马赫数段(Ma 3.0~4.5)采用Ludwieg管风洞运行模式,最高温度可达900K,可复现飞行高度的总焓和总压,有效运行时间大于150ms;高马赫数段(Ma5.0~10.0)采用激波风洞运行模式,有效运行时间大于20ms,最高驱动压力30MPa。本文通过运行方式的灵活组合,兼顾了低马赫数和高马赫数来流的不同模拟需求,实现了宽马赫数范围的试验能力。

Pulse wind tunnels are the important experimental equipment for developing hypersonic aircraft and conducting aerodynamic thermodynamic research.Based on the combination operation principle of shock wave wind tunnel and Ludwieg tube wind tunnel,a series of key technologies are broken through such as high-temperature external static heating technology,high-temperature and high-pressure gas isolation technology,and large-diameter high-temperature diaphragm design technology.The FL-63 impulse combined wide Mach number wind tunnel is designed and constructed,with a design Mach number range of 3.0 to 10.0,and adopts a combined operation mode.In the low Mach number range(Mach numbers 3.0~4.5),it adopts Ludwieg tube wind tunnel operation mode,with a maximum temperature of up to 9ook,and can reproduce the total enthalpy and total pressure at flight altitude,with an effective operating time greater than 150ms;In the high Mach number range(Mach numbers 5.0~10.0),it adopts a shock tunnel operating mode,with an effective operating time greater than 20ms and a maximum driving pressure of 3oMPa.By combining the operation modes and taking into account the different simulation requirements of low and high Mach number flow,the experimental capability of a wide Mach number range achieved.