Φ0.5m高超声速风洞气动力试验不确定评估  

Uncertainty assessment for aerodynamic test in Φ0.5m hypersonic wind tunnel

作　　者：刘春风[1] 熊琳[1] 

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《实验流体力学》2017年第4期90-96,共7页Journal of Experiments in Fluid Mechanics

摘　　要：基于AGARD(AGARD-AR-304)和AIAA(AIAA S-071A-1995)的风洞试验不确定度评估标准,对评估流程进行了扩展,应用到Φ0.5m高超声速风洞。具体包括:根据试验流程辨识得到风洞试验的不确定度源;对试验的自变量进行不确定度的评估,包括其偏差极限和精度极限的具体值;最后基于标准的方法评估了显性自变量引入的不确定度,并运用线性插值的方法评估了迎角引入的不确定度。通过一升力体外形飞行器的评估结果,发现系统误差引入的不确定度占主导地位;CN、CA和Cm3个大量的不确定度值在不同迎角时有显著差异,并且Cm的不确定度相对较大;不确定度敏感性结果显示天平和总压传感器引入的不确定度起主导作用。Based on AGARD（AGARD-AR-304） and AIAA（AIAA S-071A-1995） of wind tunnel test uncertainty assessment, the standard is extended to the Φ0.5m hypersonic wind tunnel test. The specific procedure is：distinguish all the uncertainty sources according to the test process; estimate the uncertainty of independent variables, including the value of bias limit and precision limit; finally assess the uncertainty from dominance independent variables based on the standard, and assess the uncertainty from the attack angle using the linear interpolation. The result of a lifting model shows that the systematic errors are the major contributor to the uncertainty; the uncertainty results of CN, CA and Cm are notably different at different attack angles, while the relative uncertainty of Cm has the maximum value; the sensitivity analysis shows that the uncertainty from the balance and the total-pressure probe dominates the result.

关 键 词：不确定度 偏差极限 精度极限 风洞试验 迎角 

分 类 号：V211.752[航空宇航科学与技术—航空宇航推进理论与工程]