Change the geometry. See what moved.

Caliber estimates center of pressure and static margin for a simple nose, cylindrical body, and one trapezoidal fin set. The component calculation stays visible so one final number is not the whole explanation.

Scope
This is a transparent subsonic estimate, not a full flight simulation. Verify a finished rocket with established software and launch-organization rules.

Static margin—body diameters / calibers

Waiting

Enter geometry

The result updates as dimensions change.

Rocket geometryCG in red, CP in green

Center of pressure—

Center of gravity—

CG to CP—

Total CNα—

Design notesSaved in this browser

Baseline comparisonNone saved

Set a baseline, change a dimension, and compare the result.

Component auditBarrowman-style weighting

Method and limits

The nose and fin normal-force slopes are combined into a weighted center of pressure. Static margin is reported as (CP − CG) / body diameter. The current model does not calculate drag, rail-exit speed, dynamic stability, weathercocking, motor performance, recovery, structural strength, transitions, canards, or multiple fin sets.