亚跨声速风洞短轴探管速度场校测可行性研究与验证

Feasibility study and verification of velocity field calibration for short center line probe in subsonic and transonic wind tunnel

根据GJB1179A-2012《低速和高速风洞流场品质要求》规定,速度场校测是风洞流场校测的关键项目,是评价风洞是否具备开展型号试验能力的重要依据。轴探管是用于亚跨声速风洞速度场校测的通用校测仪器。为了降低轴探管对流场的扰动,并在试验段内产生无干扰的流场,一般要求堵塞度不超过0.5%,头锥位于风洞收缩段内。近年来,随着国内2 m量级以上的大型跨声速风洞立项建设,传统的轴探管设计方案在制造、安装以及校测等方面都存在一定的困难。针对该问题,通过对轴探管头部气动外形以及安装位置的优化,削弱了轴探管头锥激波强度和扰动范围,发挥试验段加速区的消波能力,在试验段内产生了与传统长轴探管一致的无干扰流场,大大缩短了轴探管的长度,为大型跨声速风洞速度场校测的轴探管设计提供了一种可行的技术方案。

According to GJB1179A-2012"Quality Requirements for Low Speed and High Speed Wind Tunnel Flow Fields",the velocity field calibration is a key item in the wind tunnel flow field calibration and an important basis for evaluating whether wind tunnels have the ability to conduct model tests.Center line probe is a universal calibration instrument used for velocity field calibration in the subsonic and transonic wind tunnels.In order to reduce the disturbance of the center line probe on the flow field and generate an undisturbed flow field in the test section,it is generally required that the blockage degree should not exceed 0.5%,and the head cone is located in the contraction section of the wind tunnel.In recent years,with the construction of large-scale transonic wind tunnels of over 2 meters in China,traditional center line probe design schemes face certain difficulties in the manufacturing,installation and calibration.In response to this issue,the aerodynamic shape and installation position of the head of the center line probe is optimized,achieving the weakening of the intensity and disturbance range of the conical shock wave at the head of the probe,and exerting the wave attenuation ability of the acceleration zone in the test section.A non-interference flow field consistent with traditional long center line probe is generated in the test section,greatly shortening the length of the probe.The present study provides a feasible technical solution for the design of center line probe for velocity field calibration in large-scale transonic wind tunnels.