Module geometry 

Geometry-to-aerodynamics: a subsonic Barrowman subset for slender model rockets (nose cone + body tube + trapezoidal fins), implemented against the OpenRocket technical documentation and its FinSetCalc/BarrowmanCalculator sources. CP comes from the component moment sum; drag is friction + base + conical nose pressure. Supersonic values are clamped to the Mach-1 results.

Induced drag from angle of attack uses the normal-force tilt model (Cd += Cnα·α²). Not covered (deliberately): supersonic wave drag, boat-tails/transitions, and elliptical or free-form fins.

Structs

AeroAnalysis

The curves and reference quantities produced by RocketGeometry::analyze.

BodyTube

The cylindrical body tube behind the nose.

MassProperties

Dry-mass breakdown estimated from geometry and component masses by RocketGeometry::mass_properties.

NoseCone

A nose cone with length and base diameter, in metres.

RocketGeometry

The complete slender geometry.

TrapezoidalFins

Identical trapezoidal fins at the aft end of the tube. leading_sweep_m is the horizontal offset of the tip leading edge from the root leading edge.

Enums

NoseShape

Nose-cone families supported by the subset.

Functions

parse_geometry

Parse the compact geometry spec used by the CLI: nose=shape:length:diameter,tube=length:diameter,fins=count:root:tip:span:sweep:thickness. The fin thickness is optional (default 2 mm). Lengths are in metres.