avl.trim_physical
Computes aircraft trim by solving angle of attack and one control setting to achieve lift=weight and zero pitching moment about a specified CG, with bounds and residual checks.
Instructions
Prepare lift=weight and zero pitching moment about explicit CG, then verify trim. Takes SI mass/weight, density and speed plus declared geometry/CG length units. Solves alpha and one CONTROL with bounds/residual checks and independent replay. Save dimensional inputs and conversion provenance with native results, including numerical failures. Mach remains explicit. No thrust balance, mass file or eigenmodes.
Input Schema
| Name | Required | Description | Default |
|---|---|---|---|
| outputs | No | ||
| request | Yes | ||
| case_name | No | physical-trim | |
| model_path | Yes | ||
| references | No | ||
| timeout_seconds | No |