Machwave is a Python package that helps engineers design rockets, rocket motors and rocket engines with efficiency and precision.

The following assertions were taken into consideration:

• Propellant consisting of 2D BATES grain segments
• Cylindrical combustion chamber
• Thrust chamber composed of a simple flat end cap, conical nozzle and tubular casing
• Isentropic flow through nozzle
• Non-submerged nozzle
• Structure with screws as fasteners of both end cap and nozzle

Correction factors applied:

• Divergent CD nozzle angle
• Two phase flow
• Kinetic losses
• Boundary layer losses

Propellant data was obtained from ProPEP3. This software has been used in several applications/projects and it is capable of delivering reliable information on the chemical characteristics of a specific propellant composition. Burn rate data is obtained from experiments conducted by Richard Nakka and Magnus Gudnason.

• KNDX (Nakka burn rate data)
• KNSB-NAKKA (Nakka burn rate data) and KNSB (Magnus Gudnason burn rate data)
• KNSU (Nakka burn rate data)
• KNER (Magnus Gudnason burn rate data)

Correction factors.

Chamber Pressure equation.