The engine cycle deck, closed against constraints.

The design point couples the requirements that define one solved condition. For Orion, the published solution closes sea-level static net thrust at 13.34 kN, air mass flow at 16.65 kg/s, overall pressure ratio at 11.00 : 1 and turbine inlet temperature at 1320 K (1046.8 °C). The resulting TSFC is 99.3 kg/(kN·h). Each value belongs to the same solved condition.

The model basis is declared with the result. It uses Conservation of mass and energy, constant-property compressor and turbine isentropic-efficiency relations, a combustor fuel-energy balance, compressible mass-flow functions, choking at Mach 1, and momentum plus pressure thrust. The nozzle throat is solved at the design point and held fixed for altitude points; compressor-face Mach is then solved to satisfy that fixed capacity. This matters because a performance deck is only interpretable when the buyer can see what the model solved and what it held fixed.

A cycle engagement freezes the objective and constraints before the run. Pressure ratio, turbine inlet temperature, mass flow and nozzle capacity are then worked as one system. A candidate that meets thrust but misses the fuel target remains a miss. The release records that outcome against the original target.

The Orion trail begins with the supplied baseline at 4.2 : 1 overall pressure ratio and 1180 K turbine inlet temperature. It produced 12.35 kN at a TSFC of 125.3 kg/(kN·h). That line establishes the comparison basis before the redesign is judged.

The prescribed screening point raised pressure ratio to 8.5 : 1 at 1320 K. It closed at 13.25 kN and TSFC 105.0, so it missed the frozen TSFC target. The final selection moved to 11.0 : 1 at the same turbine inlet temperature, closing at 13.34 kN and TSFC 99.3. The losing point makes the selection legible.

For a buyer, that trail separates selection from assertion. It shows the supplied comparison, the candidate that failed and the point that passed. If the requirement changes, the record also shows which trade should be reopened and gives the next study a declared starting point.

A sea-level static point describes one condition. A flight mission needs solved anchors away from that design point. At 5 km / Mach 0.40, the model gives 7.93 kN thrust and TSFC 115.1 kg/(kN·h). At 10 km / Mach 0.70, it gives 5.01 kN and TSFC 123.7 kg/(kN·h). The nozzle is choked at every published point.

The same release supplies per-station total temperature, total pressure, Mach and mass flow. Those tables let a propulsion reviewer follow the gas path and give the airframe team engine-face conditions, fuel flow and thrust anchors in a form the flight model can consume.

The deliverable is the cycle deck with its assumptions, operating points and declared checks. Hardware behavior, installation losses and qualification evidence belong to later scopes with their own evidence.