Rocket science. in python.
Now pseudo.py.
- Altitude
y
- Mass dry (no fuel)
m_dry
- Mass of fuel
m_f
- Isp of rocket engin.e IN VACUMM!!!!
Isp
- Maximum engine mass flow
max_m_d
- Area of engine outlet (pi*radius^2)
A_e
- Drag coeficiant (idk look up charts online)
CD
- Bottom area of rocket (cross section (pi*radius^2))
A
- Starting vertical speed
v0
- Radius
r
- Mass
m_zeme
- Atmosphere. (Earth by default) Anything between
# oro pasi...
and# Kunas
If you dont know python. not my problem. it is intuitive Tough.
Change stg=[0,0,0]
Change anything near 1a pakopa..... 2a pakopa.... 3a pako.... 4a...
Might come Might not.
THE MATHS -> (FIZIKA.md)