Warning: X


∆V calculations are inaccurate with jet engines.

This is because the atmosphere gives them a huge diffrence in Isp depending on how high or low the engine is in the atmosphere

Understand that the following calculation is based off of the averaged Isp values from the upper and lower atmosphere.

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Alert: This website is outdated! The calculator will still work if you manually input the weights of the parts. A new website is under maintenance now.

Input:

Add Object to Calculator:
Command Pods:
Qt. Is this not used?
Propulsion:
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Command and Control:
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Structural and Aerodynamic:
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Utility and Scientific:
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Total full mass:

Total empty mass:

Isp of that stage:
Thrust: Isp: = Averaged Isp: 0

Found by finding the weighted average of all the Isp values on that stage

Solution:


In that stage, you have * m/s of ∆V
Total DV : Clear

Previous Calculations: