2D Rocket Engine — Thrust, Isp & Delta-v Simulator

Thrust0 kN

Specific impulse0 s

Δv achieved0 m/s

Propellant mass left0 kg

Mass flow rate 60 kg/s

Initial mass m₀ 20,000 kg Final (dry) mass m_f 6,000 kg

Thrust F = ṁ·v_e—

Exhaust velocity v_e—

Isp (vacuum)—

Mass ratio m₀/m_f—

Δv (theoretical, full burn)—

Δv achieved so far—

Burn time (full)—

Current mass—

Tsiolkovsky rocket equation:
v_e = I_sp·g₀ F = ṁ·v_e
Δv = v_e·ln(m₀/m_f) = I_sp·g₀·ln(m₀/m_f)

2D Canvas companion · real Tsiolkovsky rocket-equation physics