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Citing Wikipedia article on the Vertical Stabiliser:

Rudder lock occurs when the force on a deflected rudder (in a steady sideslip) suddenly reverses as the vertical stabilizer stalls. This may leave the rudder stuck at full deflection with the pilot unable to recenter it.

But how does this phenomenon occur from an aerodynamics point of view? What does it mean that the force reverses on the rudder? Is pedal force meant here? Furthermore, how can the pilot recover from rudder lock?

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Normally, the airflow over the vertical stabilizer is from front to back, which means it hits the front face of the rudder, and acts to centre it. But the vertical stabilizer is actually like a small wing. In a sideslip, the airflow comes more from the side. If you're slipping tail-right, using left rudder, the airflow comes from the right. When the vertical stabilizer stalls, the airflow is no longer acting to centre the rudder: it's just pushing against it, and pushing it away from the centre.

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  • $\begingroup$ Is it possible to recover? $\endgroup$ – Steve May 4 '18 at 16:57
  • $\begingroup$ @Steve I'm not pilot but logically to break the rudder lock the force on the rudder generated by the airflow must decrease to the point that the force that can be exerted on the rudder by the controls is greater. If the airflow can be changed with the rudder locked, then it may be possible to recover. if the rudder lock reinforces the motion of the plane that is creating the locking airflow, then probably not. $\endgroup$ – Todd Wilcox May 4 '18 at 21:30
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Rudder lock requires a mechanical linkage between the rudder pedals and the rudder. With no force on the pedals, the rudder will then weathervane (float) into an equilibrium position that depends on the sideslip angle and the hinge moment coefficients of that particular rudder.

With enough sideslip angle the rudder will hit its deflection limits and stop to move further. If the sideslip angle still increases, the difference between the maximum deflection and the theoretical floating angle (if there were no mechanical stops) will determine the aerodynamic force by which the rudder is pressed into the stops.

At this point the rudder will exhibit fully separated flow on its leeward side, but that only changes the hinge moment derivatives and the resulting floating angle. Normally, the ratio between the change in sideslip angle and the resulting change in floating angle is less that one for small angles but increases above one for larger angles. This means that the rudder will experience a steep hinge moment increase for small increases of the sideslip angle once it has reached its maximum deflection.

How far the pilot is able to overcome those forces and bring the rudder back to neutral depends on the size of the rudder and the dynamic pressure. Ideally, he/she would never allow the rudder to float, which also should ensure that sideslip angles stay low. However, in some maneuvers like a sideslip you want high sideslip angles, and there a locked rudder is quite normal.

When I was flying the Schempp-Hirth Discus, I could either float gently into a sideslip with moderate angles and no rudder lock, or violently swing the aircraft into the sideslip, which resulted in a higher trimmed sideslip angle and a locked rudder. However, rudder forces in a glider are low and ending this condition was trivially easy.

I also witnessed a crash in my career when a test flight with a marginally stable aircraft went wrong. The aircraft was flying at Mach 0.7 and had a fully mechanical rudder linkage. The pilot had taken his feet off the pedals and the aircraft went into a sideslip when he did aileron doublets. Only when the rudder deflection had reached 10° did he try to correct that condition (at this point the sideslip angle was also about 10°), but the deteriorating directional stability at higher sideslip pushed the aircraft into a maximum 27° of sideslip. Since the maximum rudder deflection was only 20°, the aircraft regained some stability with the locked rudder at the maximum sideslip angle and ended up in a yaw osciallation between 17° and 27° of sideslip. The pedal forces involved were too high to be overcome. Unfortunately, the tail was a T-tail and produced a strong pitch-down moment with those higher sideslip angles, and also the stick forces were too high to correct that. In the end, the aircraft dove into the ground.

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  • $\begingroup$ About 1.5 paragaphs in: "This is Peter Kämpf, isn't it? scroll down Yep." $\endgroup$ – StarWeaver May 6 '18 at 4:48
  • $\begingroup$ Did the accident you referred to involve the Grob SPn? $\endgroup$ – mezzanaccio May 7 '18 at 8:28
  • $\begingroup$ @mezzanaccio No, it was the Ranger 2000. $\endgroup$ – Peter Kämpf May 7 '18 at 9:55

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