Fire, under control.

One shaft. Eight compressor stages. No room for guesswork.

TEST PROGRAMME / RUN 01AUTOPILOT

T+00.0MAX DRY

DRYREHEATRECOVERDRY

THE DESIGN SHEET 01 / REFERENCE

Sea-level static · ideal gas · fuel mass neglected
Calculated here. The same model drives the engine.

PARAMETER	IDLE	MAX DRY	MAX REHEAT

● LIVE PHYSICS, NOT A LOOKUP TABLE
γ = 1.4 · R = 287 J/(kg·K) · ηc / ηt = .86 / .89
Intake loss = 0 · p₀ = 101.325 kPa · T₀ = 288.15 K

T+00.0

MAX DRY. ALL STATIONS NOMINAL.

TEST CELL: the neighbours have been told.

ENGINE ONLINE / TRUE-SCALE CUTAWAY

THE THERMODYNAMIC LOOP LIVE

— ENGINE CYCLERELATIVE TO STATION 2

ALL SYSTEMS NOMINAL

AIRFLOW—

PRESSURE RATIO—

SHAFT POWER—

SPECIFIC FUEL—

GAS-PATH TEMPERATUREKELVIN

2887001,1001,5001,950 K

↔ DRAG TO ORBIT · SCROLL TO ZOOM · AUTO ORBIT AFTER 5 s

● STATIC THRUST

—kN

MOMENTUM + PRESSURE THRUST

SPOOL SPEED / N

—%

EXHAUST TEMP / T₀₅

—K

TOTAL FUEL FLOW

—kg/s

NOZZLE EXIT / A₈

—m²

CONVERGENT NOZZLE

CHOKED FLOW

M₉ — / V₉ — m/s

THROTTLE COMMAND100.0%

IDLE / 50%↑ ↓MAX DRY / 100%

↑ ↓ throttle R reheat C cutaway B bird strike
SPACE autopilot M mute / ENGINE RUNS WITHOUT SOUND

HELIOS / TJ–72 — AN INTERACTIVE PROPULSION STUDY8-STAGE COMPRESSOR / 2-STAGE TURBINE / VARIABLE-AREA NOZZLEPHYSICS FIRST. SPECTACLE FOLLOWS.