Consider Prandtl factor

[MateusStano]

Short Description:
Implement the Prandtl factor on the Tail and Nosecone

Long Description:
Currently we have calculation of Lift Coefficient derivative in function of Mach Number through the beta parameter - see def beta in the code – only for fins. This provides a more realistic solution when the Mach number approaches 1. This dependency comes from the Prandtl factor which corrects subsonic force coefficients for compressible flow.

Implement the use of the Prandtl factor in some way in the Tail and Nosecone lift coefficient derivative calculation.

Useful Links:
https://github.com/Projeto-Jupiter/RocketPy/issues/133
https://github.com/openrocket/openrocket/releases/download/Development_of_an_Open_Source_model_rocket_simulation-thesis-v20090520/Development_of_an_Open_Source_model_rocket_simulation-thesis-v20090520.pdf