A simple yet physically comprehensive and accurate method for the estimation of the cruise fuel burn rate of turbofan powered transport aircraft operating in a general atmosphere was developed in part 1. The method is built on previously published work showing that suitable normalisation reduces the governing relations to a set of near-universal curves. However, to apply the method to a specific aircraft, values must be assigned to six independent parameters and the more accurate these values are the more accurate the estimates will be. Unfortunately, some of these parameters rarely appear in the public domain. Consequently, a scheme for their estimation is developed herein using basic aerodynamic theory and data correlations. In addition, the basic method is extended to provide estimates for cruise lift-to-drag ratio, engine thrust and engine overall efficiency. This step requires the introduction of two more independent parameters, increasing the total number from six to eight. An error estimate and sensitivity analysis indicates that, in the aircraft’s normal operating range and using the present results, estimates of fuel burn rate are expected to be in error by no more than 5% in the majority of cases. Initial estimates of the characteristic parameters have been generated for 53 aircraft types and engine combinations and a table is provided.

中文翻译：

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民用运输机巡航期间燃油消耗和其他性能特性的估计方法：第2部分，确定飞机的特性参数

第 1 部分开发了一种简单但物理上全面且准确的方法，用于估算在一般大气中运行的涡扇动力运输机的巡航燃料燃烧率。该方法建立在先前发表的工作的基础上，表明适当的归一化将控制关系减少到一组近似万能的曲线。但是，要将方法应用于特定飞机，必须将值分配给六个独立参数，并且这些值越准确，估计就越准确。不幸的是，其中一些参数很少出现在公共领域。因此，本文使用基本的空气动力学理论和数据相关性开发了一种用于它们的估计的方案。此外，扩展了基本方法以提供巡航升阻比的估计，发动机推力和发动机整体效率。这一步需要引入另外两个独立的参数，将总数从六个增加到八个。误差估计和敏感性分析表明，在飞机的正常运行范围内并使用目前的结果，在大多数情况下，预计燃油消耗率的估计误差不超过 5%。已经为 53 种飞机类型和发动机组合生成了特征参数的初步估计值，并提供了一个表格。在大多数情况下，预计燃料燃烧率的估计误差不会超过 5%。已经为 53 种飞机类型和发动机组合生成了特征参数的初步估计值，并提供了一个表格。在大多数情况下，预计燃料燃烧率的估计误差不会超过 5%。已经为 53 种飞机类型和发动机组合生成了特征参数的初步估计值，并提供了一个表格。