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Additional support for the TDK/MABL computer programAn advanced version of the Two-Dimensional Kinetics (TDK) computer program was developed under contract and released to the propulsion community in early 1989. Exposure of the code to this community indicated a need for improvements in certain areas. In particular, the TDK code needed to be adapted to the special requirements imposed by the Space Transportation Main Engine (STME) development program. This engine utilizes injection of the gas generator exhaust into the primary nozzle by means of a set of slots. The subsequent mixing of this secondary stream with the primary stream with finite rate chemical reaction can have a major impact on the engine performance and the thermal protection of the nozzle wall. In attempting to calculate this reacting boundary layer problem, the Mass Addition Boundary Layer (MABL) module of TDK was found to be deficient in several respects. For example, when finite rate chemistry was used to determine gas properties, (MABL-K option) the program run times became excessive because extremely small step sizes were required to maintain numerical stability. A robust solution algorithm was required so that the MABL-K option could be viable as a rocket propulsion industry design tool. Solving this problem was a primary goal of the phase 1 work effort.
Document ID
19930019839
Document Type
Contractor Report (CR)
Authors
Nickerson, G. R. (Software and Engineering Associates, Inc. Carson City, NV, United States)
Dunn, Stuart S. (Software and Engineering Associates, Inc. Carson City, NV, United States)
Date Acquired
September 6, 2013
Publication Date
March 19, 1993
Subject Category
COMPUTER PROGRAMMING AND SOFTWARE
Report/Patent Number
NAS 1.26:193037
T930345
SN-130
NASA-CR-193037
Funding Number(s)
CONTRACT_GRANT: NAS8-39048
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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