Originally Posted by
Bill Serger
So, are you saying that one could reasonably expect a margin of safety of 1.22*Vd, at ultimate G loading of 1.5 x limit load?
In other words, if one were flying a Utility Category aircraft with a Vne of 180 knots (.9 of Vd), a Vd of 200 knots, the pilot could expect to be safe at 244 knots (1.22*Vd) pulling 6.6 G's (1.5 * limit load)?
In that ballpark, but there's a lot not amenable to analysis which has only been tested to Vdf, and also for example a bit of turbulence at that corner of the envelope can easily push the aircraft over the edge.
I wouldn't trust my life to it, but it would be interesting to test with a model.