{
  "schema": "project33.c5.static_margin_inputs/1",
  "generator": "Simulation/static_margin.py",
  "geometry_source": "Folding Stabilized Rocket.ork",
  "units": {
    "length": "m",
    "mass": "kg",
    "time": "s",
    "static_margin": "calibers"
  },
  "geometry": {
    "d_ref": 0.0762,
    "L_n": 0.038099999999999995,
    "X_f": 0.381,
    "C_R": 0.13,
    "C_T": 0.11,
    "S": 0.18,
    "L_f_sweeplength": 0.01
  },
  "dry_mass_kg": 1.185,
  "dry_cg_m": 0.33581729957805906,
  "motor_assumed": {
    "designation": "Estes C6-5 (hard-coded)",
    "wet_kg": 0.024,
    "dry_kg": 0.011,
    "cg_m": 0.52,
    "burn_s": 1.8
  },
  "ork_motor_designation": "G64W",
  "ork_nose_shape": "ellipsoid",
  "nose_cp_coefficient_used": 0.466,
  "formula_notes": [
    "Fin CP term uses C_R/3*(C_R+2C_T)/(C_R+C_T) as the sweep term; the textbook Barrowman form uses the tip leading-edge sweep distance X_R in that position.",
    "Fin normal-force term uses the sweep length where the textbook form uses the mid-chord line length.",
    "Nose CP coefficient 0.466 is the ogive value.",
    "Only body-tube override masses are summed for dry mass."
  ],
  "cp_m": 0.457464,
  "sm_min_calibers": 1.5484,
  "sm_max_calibers": 1.5742
}