Actions for Design of a Mach-15 Total-Enthalpy Nozzle With Non-uniform Inflow Using Rotational MOC

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Design of a Mach-15 Total-Enthalpy Nozzle With Non-uniform Inflow Using Rotational MOC

Author
Gaffney, Richard L., Jr.
Published
December 28, 2004.
Physical Description
1 electronic document
Online Version

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Unclassified, Unlimited, Publicly available.
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Summary
A new computer program to design nozzles with non-uniform inflow has been developed using the rotational method of characteristics (MOC). This program has been used to design a nozzle for the NASA's HYPULSE shock-expansion tunnel for use in scramjet engine tests at a Mach-15 flight-enthalpy condition. The nozzle has an area ratio of 9.5:1 that expands the inflow from Mach 6 along the centerline to Mach 8.7. Although the density and Mach number vary radially at the exit due to the non-uniformities of the inflow, the MOC procedure produces exit flow that is parallel and has uniform static pressure. The design has been verified with CFD which compares favorably with the MOC solution.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 20050060676.
AIAA Paper 2005-0691.
43rd AIAA Aerospace Sciences Meeting and Exhibit; 10-13 Jan. 2005; Reno, NV; United States.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15963971