Unsteady Rolling Moment Characteristics for Fighter Oscillating with Yawing-Rolling Coupled Motion

Da Huang; Genxing Wu

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Unsteady Rolling Moment Characteristics for Fighter Oscillating with Yawing-Rolling Coupled Motion

机译：偏航-滚动耦合运动的战斗机非定常滚动力矩特性

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By the comparison with the results of two linear superposition models and the test results of the model in the yawing-rolling coupled oscillation, it is found that, for the configuration of aircraft discussed in this paper, the single free aerodynamic quasi-steady linear superposition principle can reflect the unsteady aerodynamic characteristics at medium and large pitch angles, such as 30 deg. However, when the pitch angle is larger than 50 deg, the single free quasi-steady aerodynamic superposition results do not match the test results for the model oscillating in the yawing-rolling coupled motion, and the quasi-steady superposition principle is not valid anymore. The unsteady aerodynamic superposition results cannot reflect the hysteresis characteristics of the yawing-rolling coupled motion even at small pitch angles. It is also shown that for a high maneuvering aircraft, the accurate unsteady aerodynamic results at large angles of attack can be obtained only by the coupled wind-tunnel tests.

机译：通过与两个线性叠加模型的结果以及该模型在偏航-滚动耦合振荡中的测试结果进行比较，发现对于本文讨论的飞机配置，单个自由气动准稳态线性叠加原理可以反映在中等和较大的俯仰角（例如30度）下的不稳定空气动力学特性。但是，当俯仰角大于50度时，单个自由准稳态空气动力学叠加结果与偏航-滚动耦合运动中振动模型的测试结果不匹配，并且准稳态叠加原理不再有效。不稳定的空气动力学叠加结果即使在较小的俯仰角下也无法反映偏航-滚动耦合运动的滞后特性。还显示出，对于机动性高的飞机，只有通过耦合的风洞试验才能获得在大迎角下的准确的非定常空气动力学结果。

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来源
《Journal of Aircraft》 |2006年第5期|p.1570-1573|共4页
作者
Da Huang; Genxing Wu;
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作者单位

Nanjing University of Aeronautics and Astronautics, 210016 Nanjing, People's Republic of China;

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收录信息美国《科学引文索引》(SCI);美国《工程索引》(EI);
原文格式 PDF
正文语种 eng
中图分类航空;
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Unsteady Rolling Moment Characteristics for Fighter Oscillating with Yawing-Rolling Coupled Motion

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