A Method for Analyzing Power-on Static Longitudinal Stability

A general method for analyzing static, longitudinal, stick-free, and stick-fixed stability is presented. The method allows for analysis of several configurations and effects of power on the stability of the airplane. A single matrix equation is used in which the total airplane lift, drag, pitching moment, and downwash are used to obtain the airplane stability.

The equations include the effects of auxiliary control devices generally used on general aviation aircraft such as downspring, bobweight, geared tab, and nonlinearities of control surface gearing.