Utilities module usage¶
[1]:
from rocketpy.utilities import *
[ ]:
%matplotlib notebook
1. Estimations for your CdS¶
[2]:
compute_CdS_from_drop_test(
terminal_velocity=10, # The desired terminal velocity (m/s)
rocket_mass=20, # kg
air_density=1.225,
g=9.80665,
)
[2]:
3.202171428571428
2. Altitude of Terminal Velocity being reached¶
[3]:
a, b, c = calculateEquilibriumAltitude(
rocket_mass=20,
CdS=5,
z0=1000,
v0=-20,
env=None,
eps=1e-3,
max_step=0.1,
seeGraphs=True,
g=9.80665,
estimated_final_time=10,
)
altitudeFunction, velocityFunction, final_sol = a, b, c


[4]:
final_sol
[4]:
{'time': 3.017253750404491,
'altitude': 972.1969610464328,
'velocity': -8.007887255820947}
[12]:
print(
f"The terminal velocity of {final_sol['velocity']:.3} m/s is reached after {final_sol['time']:.3} seconds at altitude of {final_sol['altitude']:.6} meters."
)
The terminal velocity of -8.01 m/s is reached after 3.02 seconds at altitude of 972.197 meters.