The first step in the process was to determine
the maximum dynamic pressure on the rocket. This was done by dividing the
force on the nose cone (DRAG) by it's equivalent flat plat area.
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|
|
Maximum
Drag on the rocket |
|
 |
Nose
cone drag equals 40% of the total drag and has a CD 0f 0.6 |
 |
|
The
frontal area of the nose cone |
|
 |
Maximum
Dynamic Pressure |
The next step was to determine the total area
presented to the air stream when the rocket is at a 90 angle of attack.
This will be used to determine the maximum possible loading on the
airframe.
|
 |
|
Distance from nose to Center of Pressure
Distance from the tip of the nose to the Center of
Pressure |
 |
 |
Length of the nose
cone (nose cone tip + the transitional section) |
 |
|
Equivalent length of
the nose cone |
 |
 |
Length of the body
tube component |
 |
 |
Overall equivalent
body length |
 |
|
Total area of the
rocket at 90 degrees |
 |
|
Drag |
Maximum possible loading on the rocket airframe.
|
 |
 |
This assumes a 90
degree angle of attack, and a velocity of Mach 1.25 |
