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A validation of the Joint Army/Navy Rotorcraft Analysis and Design software by comparison with H-34 and UH-60A flight test

机译：通过与H-34和UH-60A飞行测试进行比较，对陆军/海军旋翼机联合分析和设计软件进行了验证

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摘要

A detailed comparison of the output from the NPS developed Joint Army/Navy Rotorcraft Analysis and Design (JANRAD) computer code with H-34 and UH-60A flight test data was made in an effort to determine the validity of the code's predictions. Airload distribution across the rotor disk, power required at various airspeeds ranging from hover to cruise, and thrust moment were used as measures of performance. Although a quantitative comparison of airload distribution is difficult to obtain, qualitatively, the predictions are good. JANRAD's power required estimations are correct to within two percent for altitudes below six thousand feet but accuracy suffers at higher altitudes, particularly above ten thousand feet. A correlation between the variation in kinematic viscosity from sea level to ten thousand feet and the accuracy of the power predictions is demonstrated. in the case of the UH-60A, the equivalent flat plate area of the helicopter is shown to be a function of airspeed, significantly impacting the accuracy of the power required prediction. Center of gravity offset from the main rotor's axis of rotation and unsteady inflow effects influence the accuracy of thrust moment predictions.
机译：NPS开发的联合陆军/海军旋翼飞机分析和设计（JANRAD）计算机代码与H-34和UH-60A飞行测试数据的输出进行了详细比较，以努力确定代码预测的有效性。整个转子盘上的空载分布，从悬停到巡航的各种空速下所需的功率以及推力都用作性能的度量。尽管很难获得空载分布的定量比较，但从质量上来说，预测是好的。对于低于6000英尺的高度，JANRAD所需的功率估算正确至2％以内，但在更高的高度（尤其是在一万英尺以上）时，精度会受到影响。从海平面到一万英尺的运动粘度变化与功率预测精度之间的相关性得到了证明。在UH-60A的情况下，直升机的等效平板面积显示为空速的函数，这极大地影响了所需功率预测的准确性。重心偏离主旋翼的旋转轴以及不稳定的流入影响会影响推力力矩预测的准确性。

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  • 作者

    Eccles David M.;

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  • 年度 1995
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  • 原文格式 PDF
  • 正文语种 en_US
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