Wind tunnel measurement techniques for sonic boom near-field pressure

被引：0
|
作者：
Liu Z. [1 ,2 ]
Qian Z. [1 ,2 ]
Leng Y. [1 ,2 ]
Gao L. [1 ,2 ]
机构：
[1] AVIC Aerodynamics Research Institute, Shenyang
[2] Aviation Key Laboratory of Science and Technology on High Speed and High Reynolds Number Aerodynamic Force Research, Shenyang
来源：
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2020年 / 41卷 / 04期
基金：
中国国家自然科学基金;
关键词：
Near-field; Non-reflection rail; Sonic boom; Spatial averaging; Spatial pressure measurement;
D O I：
10.7527/S1000-6893.2019.23596
中图分类号：
学科分类号：
摘要：
For the sonic boom test in the intermittent supersonic wind tunnels, the accurate measurement technology for sonic boom near-field pressure is developed. Technical verification is carried out in FL-60 wind tunnel of AVIC Aerodynamics Research Institute. FL-60 wind tunnel is a trisonic blow down wind tunnel with Mach number range from 0.3 to 4.2, and the test section size is 1.2 m × 1.2 m. The test time of each run is usually tens of seconds. According to the characteristics of intermittent wind tunnels with short run time and large air consumption, a non-reflective pressure measurement rail is designed, which significantly improves the efficiency of the measurement of sonic boom near-field pressure. The CFD technology is utilized to analyze the flow characteristics of the non-reflection rail, model installation position and structure of shock wave system in the wind tunnel test section, and the feasibility of the non-reflection rail is verified. The Seeb-ALR low boom model and the self-designed axisymmetric model with jet are utilized to carry out the validation test. The high-quality measurement data are obtained by using the reference run method and spatial averaging technology as auxiliary method. The test results are in good agreement with the CFD calculation, which verifies the rationality of the sonic boom near-field pressure measurement system. © 2020, Press of Chinese Journal of Aeronautics. All right reserved.
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