SuomiKaataa2

Choosing the correct fuel-oxygen ratio depends on balancing maximum energetic performance (I sp ) with constraints on combustion temperature, materials limits, and propellant density.  In space rocket engines, the terms stoichiometric and optimal refer to the ratio of oxidizer to fuel (O/F ratio) used during combustion. While a stoichiometric mixture provides the highest potential temperature, it is almost never used in rocket engines because it is not efficient in practice. Instead, engineers use an "optimal" mixture, which balances maximum energy, exhaust velocity, and material limits.  Stoichiometric Ratio is the perfect chemical balance where there is exactly enough oxidizer to burn all the fuel completely, leaving no unreacted reactants. It produces maximum possible combustion temperature. However, the temperatures produced are usually too hot, which can melt the engine's turbine blades and combustion chamber walls. A stoichiometric mix usually creates heavier exhau...

Space rocket combustion involves rapid redox reactions between a fuel and an oxidizer, releasing high temperature gases (such as  water vapor, CO 2 and others)  and particles directly into various layers of the atmosphere.   The main types of rocket fuels are liquid hydrogen, kerosene (RP-1), liquid methane, and solid propellants, each producing different, significant air pollutants.  Rocket launches release pollutants directly into the stratosphere (approx. 12–50 km altitude), where they can persist for several years, causing ozone depletion and contributing to climate change. While currently small compared to aviation, the environmental impact of rocket emissions is disproportionately high due to the altitude of injection and the accumulation of pollutants in the upper atmosphere. Rocket propulsion; source: Wiki Let's have a look on couple of examples: 1. Liquid Hydrogen (LH 2 ) and Liquid oxygen (LOX): Used by Space Shuttle main engines, Ariane 5, the...