Originally Posted by HN39
You should read more carefully. I wrote:
Quote:
The point at M=0.5 and AoA=4.5 corresponds to (...) mass/delta=392 tonnes
OK, sorry. What
are the details of this aeroplane then? What altitude is this chart at? What is the "delta" value? The more I look at it, the less that chart makes sense.
Could you address my comment about the drag change from 0.2 to 0.8?