A worked static stability case study on a small aircraft — neutral point and static margin across the CG envelope, plus an elevator sizing check at the worst-case forward-CG, flaps-down trim condition.
The project brief: check a small single-engine aircraft's (2,450 lb MTOW, 174 ft² wing) approved 15%–35% MAC CG envelope for static longitudinal stability, then verify the horizontal tail and elevator have enough authority to trim the aircraft at every point in that envelope — including the worst-case combination of forward CG and a nose-down-pitching landing configuration. Framed as this program's baseline stability-and-control project, it walks the full sequence: neutral point from tail geometry, static margin at both CG limits, and a control-surface sizing check against the elevator's mechanical travel limit.
This module works the analysis the way a stability-and-control engineer actually would: a tail-volume-coefficient-based neutral point calculation, static margin at both the forward and aft CG limits, a trim equation solved for required tail lift and elevator deflection at the specific flight condition that demands the most control authority, and a check of that number against the elevator's mechanical limit — plus why the stability-critical CG case and the control-critical CG case turn out to be two different conditions. The full worked numbers, complete parameter table, and finished design reasoning are part of the unlocked module below.