||REDTOP-Lite Product Page
||REDTOP-Pro Product Page
||$3,999 (first year)
||Main combustion chamber and nozzle analysis only. No true power balance calculation.
||Full power balance with fluid analysis starting at pump inlet, through turbine(s), precombustion device(s), valve(s), injectors, main chamber(s), and nozzle(s)
|# of Input Parameters
||80-150 (depending on cycle modeled)
||Engine thrust, products of combustion, throat & nozzle areas, Isp, weight estimate
||Engine thrust, products of combustion, Isp, weight, reliability, cost, turbo-machinery speeds & power, internal pressures, geometries & areas, and more
||Generic staged-combustion, gas-generator, expander, tap-off, and pressure-fed cycles
||Over 20 different flowpaths and variations of staged-combustion, gas-generator, expander, split-expander, tap-off, and pressure-fed designs for "real life" engines
||Frozen and equilibrium flow analysis via minimization of Gibbs Free Energy. Approximately 30 species available in database.
||Estimation of cycle performance via expert system prediction of analogous efficiencies from historical engines
||Detailed tracking of losses based on results of power balance and fluid flowrate requirements (e.g. gas generator drive gas, etc.), heat transfer losses, etc.
||Rao nozzle analysis with flow divergence loss calculation
||Estimation of upper and lower weight ranges from assessment of major component weights and assumed cycle pressures & flowrates
||Component-level weight analysis using various physics-based, historical, or scaling relationships for engine parts and systems.
||Local implementation of the Liquid Rocket Engine Cost Model (LRECM) from NAFCOM. For Government customers only.
||Top-level estimate of engine reliability and safety