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A numerical prediction and flight test of the transient fuel temperatures in an aircraft

机译：飞机瞬态燃油温度的数值预测和飞行测试

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A numerical prediction of the transient fuel temperature in an aircraft was made and verified with a flight test. The analysis was studied with the finite difference method. Numerical calculation was performed by an explicit method of the modified Dufort-Frankel scheme. Convective heat transfer coefficients were used in calculating heat transfer between the aircraft surface and the ambient air. For an aircraft on the ground, an empirical equation represented as a function of free-stream air velocity was used. And, the heat transfer coefficient for flat plate turbulent flow suggested by Eckert was employed for in-flight phases. The governing equations used in this analysis are the mass and energy conservation equations on fuel and oils. The analysis was verified with the flight test data of a fuel system with additional fuel supplies and return concept. As a result of the verification, the difference of the fuel temperatures obtained by the analysis from those of the flight test data was relatively small with a tendency to increase in the later phases of the flight.
机译：对飞机中的瞬态燃料温度进行了数值预测，并通过飞行测试进行了验证。分析是用有限差分法进行的。通过改进的Dufort-Frankel方案的显式方法进行数值计算。对流传热系数用于计算飞机表面与周围空气之间的传热。对于地面上的飞机，使用了经验公式，该经验公式表示为自由流空气速度的函数。并且，在飞行阶段采用了Eckert建议的平板湍流传热系数。该分析中使用的控制方程是燃料和机油的质量守恒方程和能量守恒方程。该分析已通过带有附加燃油供应和回油概念的燃油系统的飞行测试数据进行了验证。验证的结果是，通过分析获得的燃料温度与飞行测试数据的温度差相对较小，并且在飞行的后期阶段趋于增加。

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