DID YOU KNOW? DTIC has over 3.5 million final reports on DoD funded research, development, test, and evaluation activities available to our registered users. Click
HERE to register or log in.
Accession Number:
AD0623401
Title:
STEADY-STATE ROCKET COMBUSTION OF GASEOUS HYDROGEN AND LIQUID OXYGEN. PART 2: ANALYSIS FOR COAXIAL JET INJECTION
Corporate Author:
ROCKETDYNE CANOGA PARK CA
Report Date:
1965-03-01
Abstract:
Simultaneous equations describing rocket propellant injection, atomization, mixing, vaporization, and combustion are formulated for a cylindrical liquid oxygen jet surrounded by an annular gaseous hydrogen stream. The formulation is based on division of the combustion chamber into a nonburning region near the injector and a combustion region further downstream. Processes in the nonburning region are required to satisfy certain combustibility criteria before combustion is possible. The propellants then pass through a plane flame front into the combustion region. A simplified treatment of turbulent mixing between unlike reacting gas streams, one of which contains a liquid oxygen spray, characterizes the combustion region model. Solutions of the system of equations, obtained with a digital computer program, are detailed, discussed, and compared favorably with experimental information from Part I.
Descriptive Note:
Research rept.
Supplementary Note:
See also AD0615798. DOI: 10.21236/AD0623401
Pages:
0139
Distribution Statement:
Approved for public release; distribution is unlimited.
Contract Number:
AF 49(638)-817
File Size:
6.39MB
