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"Performance and Properties of Liquid Propellants"

Aerojet-General Corporation, Liquid Rocket Plant

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Performance and Properties of Liquid Propellants
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Aerojet-General Corporation, Liquid Rocket Plant


If you design, build, test, or use liquid propulsion rockets, you need this reference handbook.  A perfect companion to Sutton's "Rocket Propulsion Elements," providing a handy and useful compilation of key data on virtually all liquid rocket propellants. 
 

Aerozine-50 
Ammonia 
Anhydrous Nitric Acid 
Aniline 
Bromine Pentafluoride 
Chlorine Trifluoride 
Diborane 
Diethylcyclohexane 
Ethyl Alcohol
Ehylene Oxide
Fluorine 
Hydrazine 
Monomethyl Hydrazine 
Hydrogen Peroxide 
Liquid Hydrogen 
JP-X 
Maximum Density Fuming Nitric Acid 
Red Fuming Nitric Acid 
Liquid Nitrogen
Nitrogen Tetroxide 
Nitrogen Trifluoride
Liquid Oxygen 
Ozone 
Pentaborane 
Perchloryl Fluoride 
n-Prophyl Nitrate 
RP-1 
U-DETA 
UDMH - (CH3)2N2H2 
Water 
Some of the propellants investigated

This valuable book gives the practical information you need.  It was originally researched, written, and produced in support of the U.S. Air Force TITAN missile program.  The contents are the results of more than 20 years of investigations by the world's largest propulsion contractor: Aerojet-General Corporation.   Literally millions of dollars were spent obtaining this critical yet hard-to-find data. 


Testing UDMH with RFNA, Sacramento

Originally published in June 1961 by the Technical Publications branch of the Liquid Rocket Plant of Aerojet-General, the text was prepared under the direction of Dr. C.M. Beighley, head of Aerojet's Research and Materials Department, with Dr. W.R. Fish.  We offer this high-quality digitally-restored reprint of the rare original document (Revision A, 8160-6S Copy 604, Mar 62).

It was originally intended strictly as a reference book for internal R&D engineering projects.  A few copies were shared with friendly governments abroad, and this data was used in the development of hundreds of successful rocket and missile projects. 

It's accurate, comprehensive, complete, and authoritative.  All useful liquid fuels and oxidizers are included, from Aerozine blends to UDMH. There's also a thorough presentation and discussion on computing performance, and how to apply these theoretical calculations in rocket engine design.
 
 

Aerozine-50 with Chlorine Trifloride or Nitrogen Tetroxide 

Ammonia with Liquid Fluorine, Nitrogen Tetroxide, or Liquid Oxygen 

Hydrazine with Chlorine Trifloride, Liquid Fluorine, Hydrogen Peroxide, Inhibited RFNA, Max Density FNA, Nitrogen Tetroxide, or Liquid Oxygen 

90% Hydrazine + 10% Ethylene Diamine with Nitrogen Tetroxide 

50% Hydrazine + 50% Monomethyl Hydrazine with Nitrogen Tetroxide 

Hydrazoid with Chlorine Trifluoride 

Liquid Hydrogen with Liquid Fluorine or Liquid Oxygen 

Monomethy Hydrazine with Nitrogen Tetroxide 

Pentaborane with Chlorine Trifluoride, Hydrazine, Hydrogen Peroxide, Nitrogen Tetroxide, or Liquid Oxygen 

Unsymmetrical Dimethyhydrazine with Hydrogen Peroxide, Inhibited RFNA, Max Density FNA, Nitrogen Tetroxide, Liquid Oxygen, or Perchloryl Fluoride 

60% UDMH + 40% Diethylene Triamine with Mixed Oxides of Nitrogen, Max Density FNA, or Nitrogen Tetroxide

Propellant combinations investigated in detail
 

PART I:  PERFORMANCE 

This section discusses estimating and predicting rocket engine performance from theoretical data.  Explanations include deriving throat area, chamber pressure, mixture ratio and flow rate.  Then thermochemical calculations are explained, covering curves for characteristic velocity vs mixture ratio at various pressures; combustion gas velocity vs mixture ratio for various nozzle ratios, nozzle area ratio vs mixture ratio for various nozzle pressure ratios. 

All essential algebraic formulae and equations are included, working with a wide variety of fuel-oxidizer combinations.
 


Typical page of equations and analysis



PART II:  PROPERTIES 

Individual propellants (and propellant blends) are presented in great detail, including physical properties, plus key data for vapor pressure, viscosity, thermal conductivity, heat capacity, specific gravity, and performance under various conditions. 


Typical page of detailed thermochemical, performance, and other properties (H2O2, in this case)

Long out-of-print, this new limited edition has been digitally restored and republished by the Rocket Science Institute.  Printed with a high-resolution laser printer (not photocopied) on high-quality, bright-white, acid-free paper for years of reference use.  Opens flat for convenient desk-top or lab extrapolations.  128 pages, 11" x 8-1/2" size.  ISBN 1-878628-13-5.  $29.95  Subject to availability.
 

USA (Insured Priority Mail: $3.85)
International (Priority Airmail: $9.85)

 


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