M
MERIDIAN / 06PROPULSION TEST CELL · OPEN AIR
STATIC ENGINE RUN SEA LEVEL · ISA · ZERO AIRSPEED
LIVE TELEMETRYT+00:00
AUTO
Calculated design sheet / ideal static nozzle
Reference operating points
Every column is solved from the stated cycle data.
ENGINE DATA
γ 1.40 · R 287
MODEL BASIS   Station 2: 288.15 K / 101.325 kPa · intake recovery 1.00.
Fuel mass excluded · perfect gas throughout · burn efficiencies applied to fuel heat release.
Turbine work balances compressor work only.
Live thermodynamic loop
TEMPERATURE — ENTROPY
STATIONS
2 → 3 → 4 → 5 → 7 → 9
T / Ks from station 2 / J·kg⁻¹·K⁻¹
Operator controls
REHEAT OFF
Test-cell captions
PROGRAM LOG
Pilot key
CAMERA · DRAG / WHEEL
↑↓THROTTLERREHEATCCUTAWAYBCHICKEN GUNSPACEAUTOORBIT RETURNS AFTER 5 S
GAS TEMPERATURE288 K1,950 K
TEST CELL: the neighbours have been told
TRANSIENT EVENT · RECOVERY IN PROGRESS
5.2 m SINGLE-SPOOL TURBOJET   ·   8-STAGE COMPRESSOR   ·   2-STAGE TURBINE   ·   16 PETALS
Net static thrust
— kN
MOMENTUM + PRESSURE · SEA LEVEL
Spool N
— %
LAGGED ROTOR SPEED
EGT · T05
— K
TURBINE EXIT TOTAL
Fuel flow
— kg/s
COMBUSTOR + REHEAT
Nozzle A8
— m²
EXIT STATE · —
100%
IDLEMAX
SPOOL RESPONSE · τ = 1.5 s   /   REHEAT INTERLOCK >95%