cusfbamboo.engine

Main Engine class, as well as tools for specifying engine geometry and the perfect gas model used to calculate flow properties.

References

• [1] - https://en.wikipedia.org/wiki/Nusselt_number

• [2] - https://en.wikipedia.org/wiki/Darcy_friction_factor_formulae

• [3] - https://en.wikipedia.org/wiki/Darcy%E2%80%93Weisbach_equation

• [4] - Huang and Huzel, Modern Engineering for Design of Liquid-Propellant Rocket Engines

• [5] - https://en.wikipedia.org/wiki/Radius_of_curvature

• [6] - https://en.wikipedia.org/wiki/Hydraulic_diameter

• [7] - https://mathcurve.com/courbes3d.gb/heliceconic/heliceconic.shtml#:~:text=The%20conical%20helix%20can%20be,a%20geodesic%20of%20the%20cone

• [8] - https://neutrium.net/fluid-flow/pressure-loss-from-fittings-expansion-and-reduction-in-pipe-size/

• [9] - Heister et al., Rocket Propulsion (https://doi.org/10.1017/9781108381376)

• [10] - Brkic 2012, Lambert W function in hydraulic problems (https://www.scipedia.com/public/Brkic_2012a)

Notes

• With some exceptions, coolant properties are currently evaluated at the bulk temperature, instead of the film temperature. This is because the high wall temperature can sometimes be above the coolant boiling point, which can cause errors. Ideally you would use nucleate boiling correlations in this case, but this is not always possible, and so use the bulk properties is available as a compromise.

Classes

ChamberConditions(p0, T0)	Object for storing combustion chamber thermodynamic conditions.
CoolingJacket(T_coolant_in, p_coolant_in, …)	Class for representing cooling jacket properties.
Engine(perfect_gas, chamber_conditions, geometry)	Class for representing a liquid rocket engine.
Geometry(xs, rs)	Class for representing the inner contour of a rocket engine, from the beginning of the combustion chamber to the nozzle exit.
PerfectGas(**kwargs)	Object to store a perfect gas model (i.e.
Wall(material, thickness)	Object for representing an engine wall.