"In the presence of oxygen, including atmospheric concentrations, carbon monoxide burns with a blue flame, producing carbon dioxide."
I was expecting this to be a joke like chlorine hydrogen, but the exhaust velocity falls between those of LOX hydrocarbons and LOX silane, making it actually quite good since CO is cheap as methane and dense as icosane. Ideal for armoured micromissiles?
ChemicalReaction LOX Carbon Monoxide Reactants Oxygen Carbon Monoxide ReactantCounts 1 2 Products Carbon Dioxide ProductCounts 2 ActivationEnergy_kJ__mol 33.5 AutoignitionTemperature_K 882 CharacteristicLength_m 1 - Characteristic length is a placeholder. - Autoignition temp from Wikipedia. - Activation energy from www.sciencedirect.com.sci-hub.io/science/article/pii/000926149385536W
Updating this thread to include a bunch more reactions that don't require any additional modded materials.
The bulk of this list is fluorine reactions for all the hydrocarbons that don't yet have them. Following that you'll find ammonia reactions, a fully oxidising reactions for monopropellants, and WFNA (nitric acid) reactions for the other two forms of hydrazine as well as RP-1. The nitric acid & kerosene combination (specifically as iodine-inhibited RFNA and a kerosene-gasoline mixture) was used by the Soviet RD-214 engine.
LOX-ammonia is actually quite promising since ammonia is cheap and has a very low adiabatic flame temp (allowing high thrust for a given engine size) but still a relatively high exhaust velocity among LOX mixtures.
Activation energy always seems to be difficult to find. If you are assuming IRFNA for the RP-1 reaction, you could do the same for MMH and UDMH. The activation energy values used for the N2O4 reactions with MMH and UDMH were actually for NO2. Since RFNA has some amount of NO2 it is probably more reasonable to use the N2O4 activation energy as a placeholder. Also, as I mentioned in the uncommon-hypergolic-propellents thread another source I found had WFNA/hydrazine activation energy as 21.6 kJ/mol, which is closer to other hypergolic values.
A source I used for characteristic length was the book "Liquid Rocket Engine Combustion Instability" chapter 5 table 2 which is searchable in Google books. The Long March 1 YF-1 engine uses IRFNA/UDMH and has a characteristic length of 190 cm. Characteristic Length for Nitric Acid/Hydrazine-base fuels is probably a reasonable estimate for MMH and UDHM from the table here: www.braeunig.us/space/index.htm
So, I found out something interesting about the chemical reaction definitions file. Apparently activation energy is not needed for bipropellant combustion reactions. It seems to only be used for monopropellant and explosives. You can omit the ActivationEnergy_kJ__mol line and the reaction still works in the game.
I recommend the characteristic lengths: Nitric Acid/RP-1: 2.5 meters Nitric Acid/MMH: 0.782 meters Nitric Acid/UDMH: 1.9 meters
L* is characteristic for a certain propellant combination.
For gaseous propellants
Oxygen-hydrocarbon fuels: 1.25 - 2.5 m Oxygen-hydrogen: 0.55-0.70 For liquid rocket propellants:
Huzel and Huang (1992) mention:
oxygen-kerosene: 1.02 < L* < 1.25 m oxygen-hydrogen: 0.76 < L* < 1.02 m oxygen-hydrogen (hydrogen is injected as gas): 0.56 < L* < 0.71 m nitrogen tetroxide-hydrazine based fuel: 0.60 < L* < 0.89 m hydrogen-peroxide-RP-1: 1.52 < L* < 1.78 m (including catalyst bed) Barrère et al. (1960):
oxygen- ethyl alcohol: 2.5 < L* < 3 m nitric acid - UDMH: 1.5 m < L* < 2.5 m nitric acid - hydrocarbons: 2.0 m < L* < 3.0 m Dadieu, Damm and Schmidt:
LOX - gasoline: 1.5 m < L* < 2.5 m nitric acid - UDMH: 1.5 m < L* < 2.0 m nitromethane (monopropellant): L* = 4.0 m (including catalyst bed) Humble et al (1995)
fluor-hydrogen: 0.55-0.65 m nitric acid-hydrazine: 0.75-0.90 m nitrogen tetroxide-hydrazine: 0.75-0.90 m fluor-hydrazine: 0.60-0.70 m Comments Mail to: email@example.com Created: February 2002 Last updated: 21/8/2004 (value for hydrogen-peroxide/RP-1 added)