Trim drag example doesn't do what it says

[bbrelje]

Description

The drag_polar.py example purports to have a trim drag option that can be toggled. However, it uses the OM BalanceComp to achieve this, but it doesn't have a Newton solver with which to drive the balance comp, so in effect it does nothing at all and the trim calc is wrong / not happening.

Steps to reproduce issue

Run drag_polar.py with trim drag turned on

Current behavior

CM not being balanced by tail rotation

Expected behavior

CM balanced to 0 by tail rotation

[bbrelje]

The tail is too small to actually trim the airplane at appreciable angles of attack. The Newton solver wants huge tail rotations at the outer edges of the polar