thanks... i read something,
http://www.adl.gatech.edu/classes/hi...Drag_Rise.html
the figure 0.7M is something that i found everywhere... is this the mach number till which the drag co-efficient remains the same?? whats the funda...
if u put the cruise speed and the sweepback angle of any airplane in the formula M'=M/cos (sweepback) u end up getting 0.7 again.
and whats this compressibility thing. confused about it.
i am kinda confused... have a Air india interview soon and this is their favourite
question and they really hit u hard with this...