Recent content by 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...

hahah lovely! thanks a lot man, you've really helped :P

This clears some stuff up - thanks so much for your help its really appreciated btw. so the shock wave is the result of the spontaneous change in pressure, density, temperature, speed of the airflow, energy from each is converted into a shockwave?

Ah that makes sense, thanks so much! At supersonic speeds - no stagnation points are able to be established because of the aircraft moving quicker - thus resulting in a shock wave?

Hmm that helped. In the case of an object moving through the air at sub-sonic speeds, why does the fluid set up a stagnation point?? Is it so that there is no kinetic energy, i.e so the fluid can flow over the airfoil or below the airfoil?? I'm struggling with this :(

Homework Statement Hi there, Im currently doing my A2 physics project on Supersonic flight. I am really struggling to understand the concept of Stagnation pressure, it just really hasn't clicked yet. I understand that the fluid 'responds' to pressure waves by building up stagnation pressure and...