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Analysis of film cooling in rocket nozzlesThis report summarizes the findings on the NASA contract NAG8-212, Task No. 3. The overall project consists of three tasks, all of which have been successfully completed. In addition, some supporting supplemental work, not required by the contract, has been performed and is documented herein. Task 1 involved the modification of the wall functions in the code FDNS (Finite Difference Navier-Stokes) to use a Reynolds Analogy-based method. This task was completed in August, 1992. Task 2 involved the verification of the code against experimentally available data. The data chosen for comparison was from an experiment involving the injection of helium from a wall jet. Results obtained in completing this task also show the sensitivity of the FDNS code to unknown conditions at the injection slot. This task was completed in September, 1992. Task 3 required the computation of the flow of hot exhaust gases through the P&W 40K subscale nozzle. Computations were performed both with and without film coolant injection. This task was completed in July, 1993. The FDNS program tends to overpredict heat fluxes, but, with suitable modeling of backside cooling, may give reasonable wall temperature predictions. For film cooling in the P&W 40K calorimeter subscale nozzle, the average wall temperature is reduced from 1750R to about 1050R by the film cooling. The average wall heat flux is reduced by a factor of 3.
Document ID
19940014965
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Woodbury, Keith A.
(Alabama Univ. Tuscaloosa, AL, United States)
Date Acquired
September 6, 2013
Publication Date
September 1, 1993
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NAS 1.26:194674
NASA-CR-194674
BER-596-37
Accession Number
94N19438
Funding Number(s)
CONTRACT_GRANT: NAG8-212
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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