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A method for calculating a real-gas two-dimensional nozzle contour including the effects of gammaA method for calculating two-dimensional inviscid nozzle contours for a real gas or an ideal gas by the method of characteristics is described. The method consists of a modification of an existing nozzle computer program. The ideal-gas nozzle contour can be calculated for any constant value of gamma. Two methods of calculating the center-line boundary values of the Mach number in the throat region are also presented. The use of these three methods of calculating the center-line Mach number distribution in the throat region can change the distance from the throat to the inflection point by a factor of 2.5. A user's guide is presented for input to the computer program for both the two-dimensional and axisymmetric nozzle contours.
Document ID
19750022409
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Johnson, C. B.
(NASA Langley Research Center Hampton, VA, United States)
Boney, L. R.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
September 1, 1975
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
L-10144
NASA-TM-X-3243
Accession Number
75N30482
Funding Number(s)
PROJECT: RTOP 505-11-31-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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