Trying to understand the coefficient of lift/drag of swept and unswept wings as speed increases. Some example questions and statements- A swept wing will have a lower max Cl at subsonic and supersonic speeds. I understand the lower max cl at subsonic, but the lower max cl at supersonic has confused me?
When the speed increases for a swept wing from subsonic to supersonic Mach numbers, the max CL is more or less? CL is more at supersonic and less for subsonic.
Comparing swept and unswept wings as angle of attack is increased the swept wing will produce less lift(this i understand) and more drag. Why more drag? Is it due to the span wise flow being greater?