Multistage rocket

A contemporary sketch model

Every number below is a modern illustrative assumption. The historical drawing supplies a question; the source model is an exercise in reasoning about it.

exhaustSpeed = 2000 m/s in 1500..2500 "Illustrative effective exhaust speed"
ratio1 = 3 "Assumed wet-to-final mass ratio for stage one"
ratio2 = 2 "Assumed wet-to-final mass ratio for stage two"
stage1 := exhaustSpeed*log(ratio1) [m/s]
stage2 := exhaustSpeed*log(ratio2) [m/s]
totalDeltaV := stage1+stage2 [m/s]
check budget: totalDeltaV >= 3500 m/s
sweep Exhaust: exhaustSpeed = 1500, 2000, 2500 m/s

Model limits

Ideal rocket equation only; no gravity or drag losses, burn timing, structural staging feasibility or trajectory integration.

Explore it with your agent

Create a Study, inspect the installed capabilities, and use this source as a starting point. Ask the agent to explain the equations and assumptions, then replace illustrative inputs with measured evidence for your own design.

This example includes a scalar sweep. Use napkin_sketch to add the model and napkin_run to inspect the sweep; the source editor’s scalar comparison view is for simple scenarios.