Hello Everyone!
I have a quick question regarding critical altitude. I know how critical altitude is where the wastegate is completely closed and the engine can no longer produce its rated horsepower if it continues to climb. Any thing I have read on the issue has something alone the lines of "At this point the engine will continue to loss Manifold pressure as if it was a NA engine". Which makes complete sense to me. However, at the altitude where these critical altitudes occur a lot of times over half of the atmosphere is BELOW you. So, wouldnt the engine loss manifold pressure at a MUCH slower rate due to the atmosphere not losing nearly as much pressure per 1,000 feet from when departing form sea level?? How high above critical altitude can a typical turbo powered engine fly? Thanks for the help everyone, just could not find the answer to this anywhere, figured I would come here!
FlyHigh423