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This document provides documentation for MATLAB code that computes stability and control derivatives for aircraft dynamic modeling and simulation. The code takes in basic aircraft parameters and geometry and calculates 67 constants representing the stability and control derivatives. These constants can then be used by other MATLAB programs to perform aircraft equations of motion, transfer function analysis, and dynamic simulation. The document explains how to run the MATLAB scripts and functions to generate

Author

Nurain Oke

Language

EN