Krdytkyu

up vote 2 down vote favorite 2 I'm trying to build a sounding rocket to reach the 100km as my senior project next year. To do this I need an equation to approximate the atmospheric density at any given altitude in the rocket's ascent, so that I can better understand the engine performance requirements of the rocket. I got my atmospheric data from https://www.engineeringtoolbox.com/standard-atmosphere-d_604.html Here is some python code with outputs: ## Atmospheric density curve fit from Engineering Toolbox US standard Atmosphere ## Design by whisperingShiba from scipy import optimize import numpy as np import matplotlib.pyplot as plt def fxn(x, a, b): return a*np.exp(-b*x) def polyFxn(h, a0, a1, a2, a3, a4, a5, a6, a7, a8, a9): return ((((((((a9*h + a8)*h + a7)*h + a6)*h + a5)*h + a4)*h + a3)*h +