Turbojet flow path

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.

airflow = 10 kg/s "Illustrative inlet air mass flow"
fuelFlow = 0.2 kg/s "Illustrative fuel mass flow"
flightSpeed = 100 m/s
exitSpeed = 450 m/s in 350..550 "Assumed exhaust speed"
pressureThrust = 0 N "Assumed pressure-matched exhaust"
thrust := (airflow+fuelFlow)*exitSpeed-airflow*flightSpeed+pressureThrust [N]
check thrustBudget: thrust >= 3500 N
sweep Exhaust: exitSpeed = 350, 450, 550 m/s

Model limits

An algebraic momentum balance; no compressor/turbine matching, combustion, thermal cycle or CFD.

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.