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Rocket Specific Impulse Calculator — result sheet
Calculate specific impulse and equivalent exhaust velocity from rocket thrust and propellant mass-flow rate.
Inputs used
Results
Visual chart
Breakdown
Calculation steps
Returned data table
Formula and methodology
Formula: Ve,eq = F/ṁ; Isp = F/(ṁg₀), where g₀ = 9.80665 m/s².
Specific impulse normalizes thrust by propellant weight flow, allowing propulsion performance to be compared without treating raw thrust as efficiency by itself.
This result follows the calculator's declared inputs, precision, validation boundaries, and model limits.
Input contract
- Engine thrust — N; minimum 0; maximum 1000000000000
- Propellant mass-flow rate — kg/s; minimum 1.0E-6; maximum 1000000000
Worked example
| Input | Value |
|---|---|
| Engine thrust | 100000 |
| Propellant mass-flow rate | 250 |
Equivalent velocity is 400 m/s and specific impulse is about 40.8 s.
Assumptions and limits
- Thrust and mass flow are steady averages over the same operating interval.
- The equivalent velocity includes any pressure-thrust contribution represented by the supplied thrust.
- Propellant chemistry, nozzle expansion, atmospheric variation, transient throttling, and vehicle trajectory are not modeled.
Calculator note
Source and methodology
Use the official WorldCalculate methodology policy for the source, formula, precision, and boundary standards behind this calculator.
Planning estimate, not financial, medical, legal, or professional advice. © WorldCalculate — reuse with attribution. Built and curated by Hassan ALRowaie.
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