I am aware that the stagnation point is where the air has reached a velocity of 0 and thus will stagnate creating a higher point of aerodynamic heating. This situation would most likely occur for this rocket design, but I do not know if this equation is the only one I need.
The reason for this...
I am currently helping in the design of a rocket and I am hoping to find a way to empirically calculate the heating rate on the fins. Note that these fins are located near the back of the rocket and that they are made of a fiberglass material. Also, the rocket maintains a speed of mach 1.5 for...
