The air boundary is set to at least 110cm by 110cm by 330cm where 330cm is the dimension that goes with the height of the rocket.

The front boundary condition is set to an inlet velocity of 75m/s.
The rear boundary is set to a gauge pressure of 0Pa.
All of the other boundaries were not set and therefore act as if they are a solid wall. This is why the boundary was set so large.

The material of the rocket was set to ABS Platic Molded.

Each solve was completed with incompressible flow.
Each analyzation was run to convergence, typically requiring at least 500 iterations, sometimes up to 1,000.

Drag force was calculated by summing the individual forces on each "wall" of the rocket in the direction parallel to the velocity flow.

In the "Results.txt" file, anytime there is a ~ in front of the number, 
that means the number cam from the previous model because the changes were miniscule enough to believe that the results would stay the same.
Most prominent when testing Total Drag of the rocket with No Flaps.