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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 the evaluation criteria for wind tunnel test uncertainty based on AGARD (AGARD-AR-304) and AIAA (AIAA S-071A-1995), the assessment process was extended to apply to a Φ0.5 m hypersonic wind tunnel. The method includes: identifying the source of the uncertainty of the wind tunnel test according to the test flow; evaluating the uncertainty of the test variables, including the specific values of the limit of deviation and the limit of accuracy; and finally evaluating the dominant The uncertainty introduced by the variables and the linear interpolation method were used to evaluate the uncertainty introduced by the angle of attack. The results of the evaluation of a lift-body-type aircraft showed that the uncertainty introduced by systematic errors dominates. The large number of uncertainty values of CN, CA and Cm at different angles of attack are significantly different, and the uncertainty of Cm is relatively Large; Uncertainty Sensitivity results show that the uncertainty introduced by the balance and the total pressure sensor dominates.