Run an ascent CFD trajectory through transonic and supersonic

from apex import Aether

simos = Aether(api_key=os.environ["APEX_API_KEY"])

# Mach 0.8 -> Mach 2.4 ascent on a reusable launcher. Stream the trajectory
# with drag, lift, base-pressure. The model validates each time-step against
# the supplied flight-test data and surfaces divergence with a margin estimate.
ascent = simos.simulate(
    domain="cfd",
    geometry=open("launcher.step", "rb").read(),
    geometry_format="step",
    regime={
        "mach": [0.8, 2.4],
        "altitude_km": [0, 18],
        "alpha_deg": [-2, 4],
    },
    physics=["cfd", "turbulence:sst"],
    materials={"atmosphere": "us_standard_1976"},
    flight_data="s3://my-bucket/flight_007.csv",
    validation={"target_drag_error_pct": 3.0},
    stream=True,
)

for step in ascent:
    print(
        f"t={step.time:5.2f}s  "
        f"M={step.mach:.3f}  "
        f"Cd={step.cd:.4f}  "
        f"Pb={step.base_pressure_pa:.0f} Pa"
    )
    if step.divergence_from_flight_pct > 5:
        print("  divergence > 5% — opening a margin report")