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Feasibility Study of Laboratory Simulation of Single-Stage-to-Orbit Vehicle Base HeatingThe feasibility of simulating in a laboratory the heating environment of the base region of the proposed reusable single-stage-to-orbit vehicle during its ascent is examined. The propellant is assumed to consist of hydrocarbon (RP1), liquid hydrogen (LH2), and liquid oxygen (LO2), which produces CO and H2 as the main combustible components of the exhaust effluent. Since afterburning in the recirculating region can dictate the temperature of the base flowfield and ensuing heating phenomena, laboratory simulation focuses on the thermochemistry of the afterburning. By extrapolating the Saturn V flight data, the Damkohler number, in the base region with afterburning for SSTO vehicle, is estimated to be between 30 and 140. It is shown that a flow with a Damkohler number of 1.8 to 25 can be produced in an impulse ground test facility. Even with such a reduced Damkohler number, the experiment can adequately reproduce the main features of the flight environment.
Document ID
20020033017
Acquisition Source
Ames Research Center
Document Type
Preprint (Draft being sent to journal)
Authors
Park, Chung Sik
(NASA Ames Research Center Moffett Field, CA United States)
Sharma, Surendra
(NASA Ames Research Center Moffett Field, CA United States)
Edwards, Thomas A.
Date Acquired
August 20, 2013
Publication Date
January 1, 1995
Subject Category
Spacecraft Design, Testing And Performance
Funding Number(s)
PROJECT: RTOP 242-80-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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