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首页> 外文期刊>The Aeronautical Journal >An estimation method for the fuel burn and other performance characteristics of civil transport aircraft in the cruise. Part 1 fundamental quantities and governing relations for a general atmosphere
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An estimation method for the fuel burn and other performance characteristics of civil transport aircraft in the cruise. Part 1 fundamental quantities and governing relations for a general atmosphere

机译：巡航中民用运输机的燃料燃烧和其他性能特征的估计方法。第1部分基本数量和普通氛围的理由关系

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This paper is one of a series addressing the need for simple, yet accurate, methods for the estimation of cruise fuel burn and other important aircraft performance parameters. Here, a previously published, constant Reynolds number model for turbofan-powered, civil transport aircraft is extended to include Reynolds number effects. Provided the variation of temperature with pressure is known, the method is applicable to flight in any atmospheric conditions. For a given aircraft, cruising in a given atmosphere, there is a single Mach number and Flight Level pair, at which the fuel burn per unit distance travelled through the air has an absolute minimum value. Both these quantities depend upon the Reynolds number, which, in turn, depends upon the aircraft weight and the atmospheric vertical temperature profile. Simple, explicit expressions are developed for all parameters at the optimum condition. These are shown to be in close agreement with numerical solutions of the governing equations. It is found that typical operational mass and temperature profile variations can change cruise fuel burn rate by several percent. In the International Standard Atmosphere, when the speed and altitude deviate from their optimum values, the fuel burn penalty is reduced slightly relative to the constant Reynolds number case. By way of example, the method is used to estimate the minimum fuel, speed-versus-height trajectory for cruise in a realistic atmosphere.For each aircraft, cruise fuel burn is found to be governed by six independent parameters. All are constants. Two are simple, involving only size and weight, whereas four are complex and must be determined by either theoretical, or empirical, means. The estimation of these quantities will be considered in Part 2.
机译：本文是一个系列，解决了对巡航燃料燃烧和其他重要飞机性能参数的简单且准确的方法的需求之一。这里，先前公布的涡发通行的公民运输机的恒定雷诺数模型扩展到包括雷诺数效应。如果已知压力的温度变化，则该方法适用于任何大气条件的飞行。对于给定的飞机，在给定的气氛中巡航，存在单个马赫数和飞行水平对，在该飞行级对，其每单位距离通过空气行驶的燃料燃烧具有绝对的最小值。这两种数量都取决于雷诺数，依次取决于飞机重量和大气垂直温度曲线。在最佳条件下为所有参数开发简单的显式表达式。这些被证明与控制方程的数值解相提并论。发现典型的运算质量和温度曲线变化可以将巡航燃料燃烧率的变化率变为几个百分点。在国际标准氛围中，当速度和高度偏离其最佳值时，燃料烧伤损失与常数雷诺数案例略微减小。举例来说，该方法用于估计在现实气质中巡航的最小燃料，速度与高度轨迹。对于每个飞机，发现巡航燃料燃烧被认为是六个独立参数的控制。一切都是常数。两个简单，仅涉及大小和重量，而四个是复杂的，必须通过理论或经验，方法确定。这些数量的估计将在第2部分中考虑。

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