Normal shockwave
Hey guys!
Sorry for disturbing with those questions:
Why is a normal shockwave on the upper side on a wing forming when the aircraft is in the transonic speed? Is it because the stream has not enough energy to remain supersonic on the whole upper wing section and then the subsonic area has so much drag that the normal shock wave builds up?
And whats the difference between the mach angle and the shockwave angle?
Thanks for your help!
OD