Atmospheric Descent

Simulation of atmospheric reentry of a spacecraft.

The spacecraft is 'roughly' the mass characteristics of an Apollo Command Module. The dynamic pressure is derived by 'atmosphere.m' which has been taken from Asish Tewari's book "Atmospheric and Space Flight Dynamics: Modeling and Simulation with MATLAB® and Simulink®". The start position and velocity are arbitrary - not bound by any historic mission. The aerodynamic characteristics of the craft are 'arbitrary' - I dont have the CM's actual effective surfacce area. the intent of this code is to determine the peak acceleration to see if the reentry was survivable, for given craft characteristics and start position.
Any suggestions regarding concept or code implementation would be well received.
Best Wishes,
Stephen