Aircraft performance parameters play a critical role in maintaining economic and environmental sustainability in aviation. Furthermore, the ability to calculate aircraft performance parameters accurately for the cruise range contributes to aviation in areas such as the preliminary design of aircraft and air traffic management. This study is focused on cruise range performance, as this is critical to both the evaluation and understanding of the economic and environmental impacts of commercial aircraft. Quick Access Recorders (QAR) data were used for more accurate analysis of the cruise range. The QAR data used in this study included 6,574 short-distance domestic flights by narrow-body turbofan commercial aircraft between 31 different city pairs. To obtain a more accurate cruise range equation, parameters affecting the cruise range performance were determined and studied. First, the drag polar model was improved to take the cambered profile, compressibility effects and cruise airspeeds of commercial aircraft into consideration using the real flight data. Second, Thrust-Specific Fuel Consumption (TSFC) models were compared and the most suitable one for the cruise phase was selected. After these steps, cruise range values were calculated using the Breguet range equation with these improved parameters. When the results of this enhanced range model were compared with the real flight data, the mean absolute percentage error (MAPE) was found to be 2.5% for all the Aircraft and Engine Type Groups (AETGs) considered in the data. This figure corresponds to a 7.9% smaller error than provided by previous range models based on simple parabolic drag polar and TSFC models. According to these results, the application of a simple parabolic drag polar and TSFC is not appropriate for cruise range calculations.

中文翻译：

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基于QAR数据的窄体涡扇商用飞机巡航航程预测增强

飞机性能参数在保持航空业的经济和环境可持续性方面发挥着关键作用。此外，准确计算巡航范围内飞机性能参数的能力有助于航空在飞机初步设计和空中交通管理等领域的发展。这项研究的重点是巡航范围性能，因为这对于评估和理解商用飞机的经济和环境影响至关重要。快速访问记录器 (QAR) 数据用于更准确地分析巡航范围。本研究中使用的 QAR 数据包括 31 个不同城市对之间的 6,574 次窄体涡扇商用飞机的国内短途航班。为了获得更准确的巡航距离方程，确定并研究了影响巡航范围性能的参数。首先，对阻力极地模型进行了改进，利用真实飞行数据考虑了商用飞机的弧形剖面、压缩效应和巡航空速。其次，比较了特定推力油耗 (TSFC) 模型，并选择了最适合巡航阶段的模型。在这些步骤之后，使用带有这些改进参数的宝玑航程方程计算巡航航程值。当将此增强航程模型的结果与实际飞行数据进行比较时，发现数据中考虑的所有飞机和发动机类型组 (AETG) 的平均绝对百分比误差 (MAPE) 为 2.5%。这个数字对应于一个 7。与以前基于简单抛物线阻力极地和 TSFC 模型的范围模型相比，误差小 9%。根据这些结果，简单抛物线阻力极地和 TSFC 的应用不适用于巡航距离计算。