{
  "classification": "synthetic analytical teaching model; no measurements; no uncertainty distribution",
  "boundary": "After-combustor baseline nozzle-exit station; compare stream kinetic-energy and momentum-flux changes at fixed mass flow, incoming speed, and pressure-thrust contribution. This is a steady, instantaneous vehicle-frame teaching convention, not a vehicle-dynamics model.",
  "velocity_convention": "V_infinity and V_e are positive axial flow-speed magnitudes at the inlet and nozzle-exit stations, expressed in one instantaneous vehicle-fixed frame treated as steady for this calculation.",
  "thrust_sign_convention": "F_momentum = mass_flow * (V_e - V_infinity) is reported as the forward-thrust contribution on the vehicle. A negative delta means this contribution decreases relative to the baseline. It is not the signed force on the gas.",
  "mass_flow_assumption": "The same selected mass flow is imposed at both comparison stations and in both cases. Fuel mass addition, bleed, capture/spillage changes, and flow-rate changes are not modeled.",
  "pressure_term_assumption": "The nozzle pressure-thrust term is set to zero for the displayed absolute example and held unchanged when calculating its delta. This is an imposed comparison assumption, not a consequence of energy closure.",
  "fixed_reference_case": {
    "mass_flow_kg_s": 1.0,
    "baseline_exit_speed_m_s": 2000.0,
    "incoming_speed_m_s": 1500.0,
    "generator_efficiency_assumption": 0.6,
    "auxiliary_load_kW": 12.0,
    "accelerator_bus_share": 0.7,
    "accelerator_efficiency_assumption": 0.6
  },
  "equations": {
    "initial_stream_kinetic_power_kW": "0.5 * mass_flow_kg_s * baseline_exit_speed_m_s^2 / 1000",
    "generator_electric_output_kW": "generator_efficiency * extraction_fraction * initial_stream_kinetic_power_kW",
    "generator_loss_kW": "removed_stream_power_kW - generator_electric_output_kW",
    "served_auxiliary_load_kW": "min(generator_electric_output_kW, auxiliary_load_kW)",
    "accelerator_power_returned_to_stream_kW": "accelerator_efficiency * accelerator_bus_share * max(0, generator_electric_output_kW - served_auxiliary_load_kW); an assumed lumped electric-to-directed-stream-kinetic-power conversion, not a modeled electromagnetic force field",
    "final_exit_speed_m_s": "sqrt(2 * (initial_stream_kinetic_power_kW - removed_stream_power_kW + accelerator_power_returned_to_stream_kW) * 1000 / mass_flow_kg_s)",
    "momentum_thrust_N": "forward-thrust contribution on the vehicle = mass_flow_kg_s * (positive downstream exit-speed magnitude - positive downstream inlet-speed magnitude); the displayed absolute example sets pressure thrust to zero, and its change imposes an unchanged pressure term",
    "energy_identity": "final_stream_kinetic_power + generator_loss + served_auxiliary_load + accelerator_loss + electrical_export = initial_stream_kinetic_power"
  },
  "sweep": {
    "extraction_fraction_min": 0,
    "extraction_fraction_max": 0.8,
    "step": 0.01,
    "rows": 81
  },
  "limitations": [
    "Not a complete vehicle, inlet, combustor, nozzle, MHD, or engine model; it is a defined same-stream accounting example.",
    "No measurements support slider values or selected efficiencies; they are editable teaching assumptions.",
    "Fixed mass flow, incoming speed, reference frame, baseline nozzle exit station, and pressure-thrust contribution. No added fuel mass, bleed, capture/spillage change, or changed mass flow is represented.",
    "Velocity values are positive axial speed magnitudes in a steady, instantaneous vehicle-frame convention. This is not a vehicle-dynamics model; a negative delta means the forward momentum-thrust contribution on the vehicle is lower than baseline.",
    "Pressure-thrust cancellation is an imposed assumption. Actual exit pressure, exit area, nozzle rematching/choking, and coupled pressure change are not calculated.",
    "No inlet capture or spillage, pressure drag, shock/viscous/thermal losses, conductivity, magnet mass, cooling, combustion matching, installation mass, aircraft drag, range, or fuel use.",
    "Generator and accelerator conversion losses, served auxiliaries, and electrical export are treated as sinks outside the tracked stream; dissipated heat and later interaction with the gas/vehicle are not followed.",
    "Does not represent the distinct NASA generator-before-combustor bypass cycle and does not evidence a tested integrated loop.",
    "Electrical export is energy left at the bus, not a demonstrated vehicle benefit; thrust change is only the defined momentum-flux difference.",
    "Accelerator power return is a lumped assumption that electrical input becomes directed kinetic power in this same stream. Electrode geometry, conductivity, current closure, electromagnetic body force, field generation/self-excitation, and coupling are not modeled or demonstrated."
  ],
  "verification": {
    "passed": true,
    "checks": 583,
    "method": "81-point sweep; dimensional energy closure; nonnegative loss/load/export checks; independent fixed-inlet momentum-delta identity; generated desktop/mobile SVG thrust-curve bounds; reference and endpoint/monotonicity checks."
  }
}