新型高超音速静压探针的设计和实验

DESIGN AND EXPERIMENTS OF NEW TYPES OF HYPERSONIC STATIC PROBES

关键词:  高超音速流  炮风洞  探头  压力测量

Key words:  Hypersonic flow  Gun tunnel  Probe  Pressure measurement

摘要:

参考了近40年来国外有关超音速和高超音速静压探针的研究成果,设计了多种并发展了二种高超音速静压探针。它们可精确地用于持续工作流场仅为30ms的流场静压测量。实测静压与自由流静压比p_s,m/p_s,∞=1.009;马赫数比M_∞m/M_∞,=0.993。实验在加拿大多伦多大学宇航研究院的高超音速炮风洞里完成。炮风洞喷管出口气流特性是:（空气）自由流总压比_t,∞=25.5MPa,总温T_t,∞=1000K;马赫数M_∞=8.30;自由流静压p_s,∞=2.13kPa;雷诺数R_e=3.2×10⁷。以探针直径D为基准的R_e,D=34,000～52,800。这种探针己被用于“管内高超音速流场发展实验研究”中了。

Abstract:

By refering to experimental results of hypersonic and supersonic static probes developed during the past 40 years in the world, several types of hypersonic static probes were designed and tested, two of whichwere developed. They can be used to accurately measure ststic pressures of hypersonic flow which has oaly useful workiag time of 30ms. By use of new types of static probes, the ratio of measured static pressure to the free-strema static pressure ps, m/ps, ∞ = 1.009, and the ratio of Mach number M∞, m/M∞ = 0.993. The experiments were made in the Hypersonic Gun Tunnel of UTIAS in Canada. The flow properties of the gun tunnel are as following: total pressure of free-stream pt,∞ = 25.5MPa,total temperature Tt,∞= 1000K, Reynolds number Re = 3.2 ×107/M, ReD = 34,000-52,800, based on probe D.Now the new types of hypersonic static probe are successfully used in the project of "The Experimental Investigation of Deve-lopmens of Hypersonic Flow in a Pipe" in UTIAS.