NDLI: Numerical methods for the calculation of three-dimensional nozzle exhaust flow fields

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Numerical methods for the calculation of three-dimensional nozzle exhaust flow fields

Content Provider	NASA Technical Reports Server (NTRS)
Author	Delguidice, P. D. Dash, S. M.
Copyright Year	1975
Description	Numerical codes developed for the calculation of three-dimensional nozzle exhaust flow fields associated with hypersonic airbreathing aircraft are described. Both codes employ reference plane grid networks with respect to three coordinate systems. Program CHAR3D is a characteristic code utilizing a new wave preserving network within the reference planes, while program BIGMAC is a finite difference code utilizing conservation variables and a one-sided difference algorithm. Secondary waves are numerically captured by both codes, while the underexpansion shock and plume boundary are treated discretely. The exhaust gas properties consist of hydrogen-air combustion product mixtures in local chemical equilibrium. Nozzle contours are treated by a newly developed geometry package based on dual cubic splines. Results are presented for simple configurations demonstrating two- and three-dimensional multiple wave interactions.
File Size	1517266
Page Count	43
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19760002942
Archival Resource Key	ark:/13960/t5m950k0c
Language	English
Publisher Date	1975-01-01
Access Restriction	Open
Subject Keyword	Aerodynamics Exhaust Nozzles Exhaust Flow Simulation Three Dimensional Flow Nozzle Flow Hypersonic Aircraft Prediction Analysis Techniques Computer Programs Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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