Parameters
Presets
Multi-stage mode
Specific impulse Isp [s]
300
Solid ~250 / Kerosene ~320 / LH₂ ~450
Initial mass m₀ [kg]
10000
Final (dry) mass m_f [kg]
2000
Dry mass (excluding propellant)
Gravity losses [m/s]
1200
Drag losses [m/s]
150
—
Total ΔV [m/s]
—
Net ΔV [m/s]
—
Mass ratio m₀/m_f
—
Propellant fraction
Theory
Tsiolkovsky rocket equation (single stage):
$$\Delta v = I_{sp}\, g_0 \ln\!\left(\frac{m_0}{m_f}\right)$$Multi-stage rocket (sum of stages):
$$\Delta v_{total} = \sum_{i} I_{sp,i}\, g_0 \ln\!\left(\frac{m_{0,i}}{m_{f,i}}\right)$$$g_0 = 9.80665\ \text{m/s}^2$, specific impulse $I_{sp}$ in [s]
Astrodynamics applications: Hohmann transfer ΔV budgeting / multi-stage propellant mass optimization / propulsion system selection (solid/liquid/electric) / mission analysis in GMAT or STK.