16 lines
1020 B
Plaintext
16 lines
1020 B
Plaintext
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.
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The front boundary condition is set to an inlet velocity of 75m/s.
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The rear boundary is set to a gauge pressure of 0Pa.
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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.
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The material of the rocket was set to ABS Platic Molded.
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Each solve was completed with incompressible flow.
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Each analyzation was run to convergence, typically requiring at least 500 iterations, sometimes up to 1,000.
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Drag force was calculated by summing the individual forces on each "wall" of the rocket in the direction parallel to the velocity flow.
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In the "Results.txt" file, anytime there is a ~ in front of the number,
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that means the number cam from the previous model because the changes were miniscule enough to believe that the results would stay the same.
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Most prominent when testing Total Drag of the rocket with No Flaps. |