turbo_moc.geometry.rotor_geometry module#
Adapt the unchanged vortex solver to the common conformal blade geometry.
The solver’s x is downstream and y is tangential. The shared numerical chart uses q = (y, -x), with clockwise tangential angle and downstream-negative q_y. Only a similarity transform is applied to the blade. Annular pitch comes from the blade count; a linear cascade preserves the solver’s natural pitch/chord.
- turbo_moc.geometry.rotor_geometry.build_rotor_design(rotor_result, config)[source]#
Return a canonical Design from one completed vortex-flow blade solution.
Solver lengths may be metres or sonic-radius units: the common chord normalization removes that scale. No thermodynamic or vortex calculations are repeated during geometry, span mapping, or mesh generation.