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A shock wave capability for the improved Two-Dimensional Kinetics (TDK) computer programThe Two Dimensional Kinetics (TDK) computer program is a primary tool in applying the JANNAF liquid rocket engine performance prediction procedures. The purpose of this contract has been to improve the TDK computer program so that it can be applied to rocket engine designs of advanced type. In particular, future orbit transfer vehicles (OTV) will require rocket engines that operate at high expansion ratio, i.e., in excess of 200:1. Because only a limited length is available in the space shuttle bay, it is possible that OTV nozzles will be designed with both relatively short length and high expansion ratio. In this case, a shock wave may be present in the flow. The TDK computer program was modified to include the simulation of shock waves in the supersonic nozzle flow field. The shocks induced by the wall contour can produce strong perturbations of the flow, affecting downstream conditions which need to be considered for thrust chamber performance calculations.
Document ID
19850011050
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Nickerson, G. R.
(Software and Engineering Associates, Inc. Santa Ana Heights, CA, United States)
Dang, L. D.
(Software and Engineering Associates, Inc. Santa Ana Heights, CA, United States)
Date Acquired
September 5, 2013
Publication Date
March 1, 1984
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
NASA-CR-171302
SN-55
NAS 1.26:171302
Report Number: NASA-CR-171302
Report Number: SN-55
Report Number: NAS 1.26:171302
Accession Number
85N19360
Funding Number(s)
CONTRACT_GRANT: NAS8-34974
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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