Learn · Jet Propulsion
Nine illustrated, worked-through articles — from “thrust is momentum” to the cycle analysis behind every gauge in the six engine demos. The standard atmosphere, the Brayton cycle, bypass, shaft power and supersonic ram compression, all derived.
Start from the beginning →Station numbers, total temperature, and deriving η = 1 − 1/(τr·τc) — Otto’s twin at constant pressure.
04The full τ-notation solution: work balance, exit velocity, specific thrust, fuel/air ratio and TSFC.
05Why moving more air slower wins: the fan work balance, the two-stream thrust equation, and α’s limits.
The free power turbine, shaft power and PSFC, thrust = ηP/V₀, and why propellers give up near Mach 0.7.
07Thermal × propulsive = overall; TSFC as its mirror; and the Breguet range equation tying it to L/D.
08Ram compression, zero static thrust, the τr → τλ ceiling, and why hypersonic flight burns supersonically.