Oblique + Normal Compression shock and nose cone angles

[mikeyboy22]

Hi there.
I'm using the following equations as part of my physics research paper:
http://www.grc.nasa.gov/WWW/K-12/airplane/normal.html
The initial equation, concerning the half angle of the nose cone of the object, gives me a rather trivial answer at mach 1.5..
a > 0.199 (3sf)
Now, anything over 0.199 degrees gives a normal shock right? But anything below gives an oblique shock.
What are the normal nose cone angles for supersonic combat aircraft?? Are they below or above this? If above, does this mean Supersonic aircraft experience a normal shock at the nose? But an oblique shock at the knife edge wings?

 

[Illmatic1]

Thanks The normal nose cone angle for supersonic combat aircraft is typically greater than 0.199 degrees. This means that it will experience a normal shock at the nose when flying at Mach 1.5 and above. However, since the wings of these aircraft are usually designed with sharp edges (known as knife-edge wings), they may still experience an oblique shock at lower speeds.