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Issue #01: team-02 - Add aero surface info to Rocket.allinfo() #99

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Issue #01: team-02 - Add aero surface info to Rocket.allinfo() #99

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084d6b7
Add aero surface info to Rocket.allinfo()
SullivanMuse Aug 27, 2022
2e4b504
Implement dispersion analysis plotting utilities
SullivanMuse Aug 28, 2022
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43 changes: 41 additions & 2 deletions rocketpy/Rocket.py
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Original file line number Diff line number Diff line change
Expand Up @@ -690,6 +690,16 @@ def finNumCorrection(n):
"cl": cl,
"roll parameters": rollParameters,
"name": "Fins",
'addFins parameters': {
'n': n,
'span': span,
'rootChord': rootChord,
'tipChord': tipChord,
'distanceToCM': distanceToCM,
'radius': radius,
'cantAngle': cantAngle,
'airfoil': airfoil,
},
}
self.aerodynamicSurfaces.append(fin)

Expand Down Expand Up @@ -960,8 +970,37 @@ def allInfo(self):
+ "{:.3f}".format(self.centerOfMass(0))
+ " m"
)
print("\nAerodynamic Components Parameters")
print("Currently not implemented.")

# Print Aerodynamic Components Information
print("\nAerodynamic Components")
print(self.aerodynamicSurfaces)
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I would suggest a minor change here so the user can better visualize the outputs:

Suggested change
print(self.aerodynamicSurfaces)
for surface in self.aerodynamicSurfaces:
if 'name' in surface:
print(surface['name'])
else:
print('Unnamed Surface:')
print(surface)

for index, surface in enumerate(self.aerodynamicSurfaces):
# Get aerodynamic surface prefix
# If Surface has a name, print it alongside the index
if 'name' in surface:
name = surface['name']
prefix = f"\nAerodynamic Surface {index} \"{name}\" parameters"
else:
prefix = f"\nAerodynamic Surface {index} parameters"
print(prefix)

# Print possible parameters
if 'cp' in surface:
print(f"Center of Pressure Location: {surface['cp']}")
if 'cl' in surface:
print(f"Coefficient of Lift:")
surface['cl']()

# Print parameters specific to fins
if 'addFins parameters' in surface:
parameters = surface['addFins parameters']
print(f"Number of Fins: {parameters['n']}")
print(f"Fin Span (m): {parameters['span']}")
print(f"Fin Root Chord (m): {parameters['rootChord']}")
print(f"Fin Tip Chord (m): {parameters['tipChord']}")
print(f"Fin Distance from Fin Leading Edge Geometric Center to Rocket Unloaded Center of Mass (m): {parameters['distanceToCM']}")
print(f"Fin Root Radius from Center of Rocket (m): {parameters['radius']}")
print(f"Fin Cant Angle with Respect to Rocket Centerline(deg): {parameters['cantAngle']}")

# Print rocket aerodynamics quantities
print("\nAerodynamics Lift Coefficient Derivatives")
Expand Down