Center of Pressure
Our rocket design team needed to calculate center of pressure to figure out whether our model rocket would fly. Documentation for this progress is shown below.
***All Measurements were made using inches***
Equation: (SA) CP = (Surface Area of Nose) (D1) + (Surface Area of Body) (D2) + (Surface Area of Fins) (D3)
D1 = Distance from the bottom of the rocket to the center of the nosecone
D2 = Distance from the bottom of the rocket to the center of the body
D3 = Distance from the bottom of the rocket to the center of the fins
Solving the Equation:
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The equation shown below is our revised center of pressure (after we modified the rocket, due to weight issues). To see more on how we modified our rocket, go to our "Weight Modifications" page, which is directly under the Center of Pressure page in the Rocket Design tab. Other than that, check out our final center of pressure equation work that is shown below.
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(SA) CP = (Area of Nose) (D1) + (Area of Body) (D2) + (Area of Fins) (D3)
(SA) CP = (15.75) (8.25) + (68.03512) (3.25) + (54.9829) (1.25)
(SA) CP = (129.9375) + (221.11414) + (68.72825)
(SA) CP = 409.780265
(138.76802) CP = 409.780265
CP = 2.95298776
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Our Center of Pressure was 2.95298776! This is good because our fins end 3 inches above the bottom of the rocket, and this is below our newly calculated center of pressure.
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This is the original equation, and our center of pressure was 6.091699559. This was good, since our rocket was about twice as tall.
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(SA) CP = (Area of Nose) (D1) + (Area of Body) (D2) + (Area of Fins) (D3)
(SA) CP = (26.96435) (9.5) + (118.193) (6.5) + (30.5397) (1.5)
(SA) CP = (256.351325) + (768.25281) + (45.8094825)
(SA) CP = 1070.413618
(175.716745) CP = 1070.413618
CP = 6.091699559
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