Wind tunnel oscillatory testing is a technique conventionally used for the measurement of dynamic aerodynamic loads on subscale aircraft models. Oscillatory testing is commonly used for identification of dynamic stability derivatives for flight mechanics models. Model oscillation is normally driven by a rig drive mechanism, or with the use of its control surfaces. This paper presents a new test technique in which self-induced coupled roll and yaw oscillations are driven purely by the aircraft’s natural modes of motion when constrained in translation and in pitch rotation. This method does not require external mechanisms to drive the motion, nor the use of aircraft control surface inputs to sustain the oscillation. Without these sources of error, it is potentially advantageous for identification of dynamic stability derivatives using parameter estimation techniques. The mechanics of and requirements for this self-induced oscillation are discussed. Computational simulation and dynamic wind tunnel tests of a subscale BAe Hawk model are used to demonstrate the self-induced roll–yaw oscillations and their results are compared. Effects of varying parameters such as wind tunnel speed and the addition of spring stiffness onto the aircraft rotation axes on the frequency and stability of the oscillation are investigated.

风洞振荡测试是一种常规用于测量小型飞机模型动态空气动力载荷的技术。振荡测试通常用于识别飞行力学模型的动态稳定性导数。模型振荡通常由钻机驱动机构驱动，或使用其控制面驱动。本文提出了一种新的测试技术，其中当平移和俯仰旋转受到限制时，自感应耦合滚转和偏航振荡完全由飞机的自然运动模式驱动。这种方法不需要外部机构来驱动运动，也不需要使用飞机控制面输入来维持振荡。如果没有这些错误来源，使用参数估计技术识别动态稳定性导数具有潜在的优势。讨论了这种自感振荡的机制和要求。使用亚尺度 BAe Hawk 模型的计算模拟和动态风洞测试来演示自感应横滚偏航振荡，并比较它们的结果。研究了风洞速度等不同参数和飞机旋转轴上增加的弹簧刚度对振荡频率和稳定性的影响。