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nozzle-design

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Conceptual design and analysis of a liquid-propellant rocket engine for orbital launch vehicles. Presents key specs (chamber pressure, nozzle expansion, thrust-to-weight), propellant/material selection (LOX/RP-1 & LOX/LH₂), cycle considerations, and computational workflows for engine sizing, sweeps and trade-off studies.

  • Updated Nov 6, 2025
  • Python

80 validated aerospace-engineering tools for Python, the CLI, and MCP agents: structures, aerodynamics, compressible flow, propulsion, orbital mechanics, ascent and recovery, optimization, and reliability. Every result is traceable to a published reference.

  • Updated Jul 25, 2026
  • Python

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