Module geometry 

Geometry-to-aerodynamics: a Barrowman subset for slender model rockets (nose cone + body tube + trapezoidal fins), implemented against the OpenRocket technical documentation and its FinSetCalc and SymmetricComponentCalc sources. CP comes from the component moment sum (with the supersonic aft shift); drag is friction + base + nose wave drag

• rounded-fin form drag. The fin normal-force slope uses Diederich below Mach 1, the Busemann K1 term above Mach 1.5, and OpenRocket’s Hermite join between them.

Induced drag from angle of attack uses the normal-force tilt model (Cd += Cnα·α²). Not covered (deliberately): boat-tails/transitions, elliptical or free-form fins, fin-body interference drag, and wave drag of elliptical/parabolic noses past Mach 1 (conical and ogive are fully modelled).

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.