Aviator 25 - Just want to add one more since this page is where you've got plenty of helpful info for your plane beginning from a post right after your test flight report. Now also including highlights and hot topic... I agree that speedracerntrixie is expert on this plane but pimmnz is correct on his evaluation that speedracerntrixie actually didn't notice that support his analysis.

speedracerntrixie - you always misunderstood us here, you don't know how to appreciate others comment, I commented that the latest input right after I left was an expert advice. But I don't want to exclude pmzz and cfircav8r becuase their input are also correct and valuable too.

I share my hornet because to show you all of you are correct as elevator is very dependent with airspeed even if it's nose heavy, becuase the aircraft we are talking about is nose heavy and has increase weight and power. I'm sport minded person and about to congratulate you for leading this thread having the best advice for now and for Aviator 25 on solving the problem but how would you get the joy of helping if all the guys don't want to reply your comment anymore. This thread is becoming more interesting because of them also.

Here's how it goes for me, the pitch moment cause by the elevator is affected by airspeed at exponential rate while CG is linear. When aircraft is on high AOA and descending, the resultant air stream on the tail can be influence by the propeller, horizontal wind and air flow caused by descending slope. The tail plane with no camber produce lift relative to air stream because of its AOA. When there's elevator input the tail wing has negative camber which produces down lift relative to airspeed. When CG is located at 25% of MAC and C/L reaches at the same point, the elevator for steady state must be zero lift but it is very difficult to have zero lift without precision equipment. At this time the elevator can easily be influenced by above air stream factors. Because airflow has exponential factors and there's no counter force that controls pitch acceleration. Because of the high drag and lift employed by high AOA the aircraft couldn't maintain its airspeed without stall eventually. As per speedracerntrixie mentioned the elevator loses it's down wash and give up to take over by the underneath wind caused by fall as pimmnz mentioned and generates pitch down moment to the entire aircraft. The solution I'm thinking about is to reduce AOA slightly as per mentioned before with the latest CG then increase on flaring.