First flight after some time.
AUW is now 1400g from the before ~800g.
6s 5200, 10x6, 580kv.
Again calculated PIDs for Q_roll with Ziegler/Nichols method but they were not usable because of oscilations. Had to manually reduce them. For hover pitch and yaw I used the same PIDs as I used in my earlier videos and It seems to work. Did not try to retune them.
In Horizontal flight you see the yaw drift while doing the transition.
Then you can see enormous oscilations in both roll and pitch. They increase with speed. Log said that it had a maximum of ±11g (!!!) where I put full throttle and went to about 28 m/s.
I dont think that I will be able to make this more stable in horizontal flight and still use the symmetrical airfoil (NACA 0015).