To achieve supermaneuverability, the flight envelope for modern fighter aircraft should be extended beyond 40 \(\sim \)60° angles of attack region, where unstable and undesirable flight characteristics such as wing rock may occur. This paper investigates the wing rock phenomenon of a fighter configuration having conventional conical forebody through free-to-roll (FTR) wind tunnel tests. The time history of roll angle measurements were analyzed to examine the factors affecting the wing rock. Flow visualization and static wind tunnel tests were also carried out to better understand the cause of the wing rock phenomenon. The experimental results indicate that the vortices originated from forebody and their interactions with strake and wing vortices are the main causes of the wing rock phenomenon, and that the directional instability of the aircraft triggers the limit cycle oscillation rather than the lateral instability. Preparatory shape modification study was conducted to identify the way of alleviating wing rock. The chine shape applied along conical forebody has a great effect on reducing the wing rock by decreasing dynamic hysteresis of the forebody vortex movement. The dynamic test methodology presented in the paper can greatly reduce the risks and cost required for aircraft development projects by enabling the identification of undesired dynamic characteristics, such as wing rock, early in the design phases.

为了实现超机动性，现代战斗机的飞行包线应扩展到40 \（\ sim \）攻角为60°，可能会出现不稳定和不良的飞行特性（如机翼岩石）。本文通过自由滑（FTR）风洞测试研究了具有常规圆锥形前身的战斗机构型的机翼岩石现象。分析了侧倾角测量的时程，以检查影响机翼岩石的因素。还进行了流动可视化和静态风洞测试，以更好地了解机翼岩石现象的原因。实验结果表明，起源于前体的涡旋以及它们与风向和机翼涡旋的相互作用是机翼岩石现象的主要原因，并且飞机的方向不稳定性触发极限循环振荡，而不是横向不稳定性。进行了预备的形状修改研究，以确定减轻机翼岩石的方法。沿圆锥形前体施加的弦形状通过减小前体涡旋运动的动态滞后作用，对减小机翼岩石具有很大的作用。本文提出的动态测试方法可以在设计阶段的早期就识别出不希望的动态特性，例如机翼岩石，从而可以大大降低飞机开发项目所需的风险和成本。