Nozzle — MOC Rocket Nozzle Design Tool
Method of Characteristics solver for axisymmetric supersonic nozzle design
Loading Pyodide and dependencies...
Exit Mach Number
Expansion Ratio (A/A*)
Gamma (γ)
Throat Radius (mm)
Conical
Half-angle:
deg
Rao Bell
Bell fraction:
%
MLN
Characteristics:
TIC
Characteristics:
Truncation:
%
Length-Constrained
Target length (r*):
Characteristics:
Optimal truncated MLN for length budget
Sivells
rc:
θ
infl
:
upstream contour only (throat → inflection)
Custom
CSV file:
Two columns: x, y (throat at min y)
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Contour Comparison
Performance
Nozzle
Cf
% Ideal
Notes
Run a design to see results
Exit Plane Mach Distribution
Tolerance Band Analysis
Export:
Export YAML Config