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Ablative material testing for low-pressure, low-cost rocket enginesThe results of an experimental evaluation of ablative materials suitable for the production of light weight, low cost rocket engine combustion chambers and nozzles are presented. Ten individual specimens of four different compositions of silica cloth-reinforced phenolic resin materials were evaluated for comparative erosion in a subscale rocket engine combustion chamber. Gaseous hydrogen and gaseous oxygen were used as propellants, operating at a nominal chamber pressure of 1138 kPa (165 psi) and a nominal mixture ratio (O/F) of 3.3. These conditions were used to thermally simulate operation with RP-1 and liquid oxygen, and achieved a specimen throat gas temperature of approximately 2456 K (4420 R). Two high-density composition materials exhibited high erosion resistance, while two low-density compositions exhibited approximately 6-75 times lower average erosion resistance. The results compare favorably with previous testing by NASA and provide adequate data for selection of ablatives for low pressure, low cost rocket engines.
Document ID
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Richter, G. Paul
(NASA Lewis Research Center Cleveland, OH, United States)
Smith, Timothy D.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 6, 2013
Publication Date
October 1, 1995
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NAS 1.15:107041
Meeting Information
Meeting: Combustion Subcommittee, Propulsion Systems Hazards Subcommittee
Location: Huntsville, AL
Country: United States
Start Date: October 23, 1995
End Date: October 27, 1995
Accession Number
Distribution Limits
Work of the US Gov. Public Use Permitted.
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