Lox/Alcohol
RD-100 / RD-101
Credit - © Dietrich Haeseler
Propellant Formulation: LOX/Alcohol-75%. Optimum Oxidiser to Fuel Ratio: 1.43. Temperature of Combustion: 3,230 deg K. Density: 1.01 g/cc. Isp (sl): 282. Isp (vac): 297.
Propellant Formulation: LOX/Alcohol-92.5%. Optimum Oxidiser to Fuel Ratio: 1.73. Temperature of Combustion: 3,390 deg K. Density: 0.99 g/cc. Isp (sl): 284. Isp (vac): 338.
Propellant Formulation: LOX/Alcohol-96%. Optimum Oxidiser to Fuel Ratio: 1.80. Temperature of Combustion: 3,420 deg K. Ratio of Specific Heats: 1.21. Density: 0.98 g/cc. Characteristic velocity c: 1,710 m/s (5,610 ft/sec). Isp Shifting: 288 sec. Isp Frozen: 276 sec. Pp Isp Shifting: 282. Mol: 24.10 M (79.00 ft).
Oxidiser: LOX. Oxidiser Density: 1.140 g/cc. Oxidiser Freezing Point: -219 deg C. Oxidiser Boiling Point: -183 deg C.

Liquid oxygen was the earliest, cheapest, safest, and eventually the preferred oxidiser for large space launchers. Its main drawback is that it is moderately cryogenic, and therefore not suitable for military uses where storage of the fuelled missile and quick launch are required. Liquid oxygen, as normally supplied, is of 99.5 percent purity and is covered in the United States by Military Specification MIL-P-25508. High purity liquid oxygen has a light blue colour and is transparent. It has no characteristic odour. Liquid oxygen does not burn, but will support combustion vigorously. The liquid is stable; however, mixtures of fuel and liquid oxygen are shock-sensitive. Gaseous oxygen can form mixtures with fuel vapours that can be exploded by static electricity, electric spark, or flame. Liquid oxygen is obtained from air by fractional distillation. The 1959 United. States production of high-purity oxygen was estimated at nearly 2 million tonnes. The cost of liquid oxygen, at that time, ex-works, was $ 0.04 per kg. By the 1980's NASA was paying $ 0.08 per kg.


Fuel: Alcohol. Fuel Density: 0.870 g/cc. Fuel Freezing Point: -114 deg C. Fuel Boiling Point: 78 deg C.

Alcohol (C2H5OH) was the fuel used for the German V-2 rocket, and the first derivative rocket engines in the United States, Soviet Union, and China used it as well. Better performance was achieved by increasing the alcohol concentration in the post-war engines. But after better-performance rocket-grade kerosene was developed by Rocketdyne in the REAP program of 1953, use of alcohol was abandoned. Ethyl alcohol, or ethanol, has wide commercial uses in both the chemical and the spirits industries and is produced commercially in large quantities. It is a clear, water-white, mobile liquid with the characteristic alcohol odour. It is an excellent solvent; special lubricants must be used. Materials of construction used for methanol are also used for ethanol. Like methanol, ethanol forms explosive mixtures with air or with oxidisers. Denaturants added to the alcohol can cause poisoning, blindness, and death. (Despite this, the Russians liked to call their early missiles 'drunk rockets'. Ethyl alcohol is produced by fermentation of sugars (glucose) or hydrolysed starches. The majority of the ethyl alcohol for solvent use is made by the hydrolysis of ethyl sulphate, which results from the addition of sulphuric acid to ethylene. Ethyl alcohol forms an azeotrope with water; this solution is 95.6 per cent ethyl alcohol. Absolute alcohol is made by azeotropic distillation with benzene. The estimated 1959 United States production was 1.6 million tonnes (50 per cent by volume). The price of absolute alcohol, tax-free, in tank-car quantities was $ 0.16 per kg. Density varies: 0.87 g/cc for 75% alcohol; 0.80 g/cc for 92.5% alcohol; to 0.79 g/cc for 96% alcohol.


Engines Using Lox/Alcohol
Engine
engineslink
Thrust(vac)
kN
Thrust(sl)
kN
Isp
sec
Isp (sea level)
sec
Designed for Status
RD-103RD         First Stages Out of Production
XLR-71-NA-1   533.700   245   Development cancelled 1955.
Garvey Aerospike         First Stages Development ended 2005
RD-3A   390.000   214 First Stages Out of Production
XLR-11   26.670     First Stages Out of Production
LR-8-RM-5   26.670     First Stages Out of Production
LR39 0.225          
XR3A2 0.700       First stages Hardware
XR4A3 1.780       First stages Hardware
RD-0101 39.200   255   First Stages Out of Production
XLR-25-CW-1 66.880       First Stages Out of Production
A-9 288.700 249.100 255 220 Upper Stages Study 1942
RD-100 304.000 267.000 237 203 First Stages  
A-4 311.800 264.900 239 203 First Stages  
XLR-43-NA-1 333.000         Development completed 1951
RD-101 404.000 363.000 237 210 First Stages  
A-6 414.300 367.400 265 235 First Stages Out of production
RD-102 428.000   235 214 First Stages Development ended 1951
RD-103 500.000 432.000 243 216 First Stages Out of Production
RD-103M 500.100 432.000 248 220 First Stages  
Sled Technology 666.000          
Sanger-Bredt Sled 1,144.100 980.600 245 210 First Stages Study 1943
A-10 2,306.800 1,961.300 247 210 First Stages Study 1942
 
 
 
 
 
 
 
 
 

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