NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
A model of transverse fuel injection applied to the computation of supersonic combustor flowA two-dimensional, nonreacting flow model of the aerodynamic interaction of a transverse hydrogen jet within a supersonic mainstream has been developed. The model assumes profile shapes of mass flux, pressure, flow angle, and hydrogen concentration and produces downstream profiles of the other flow parameters under the constraints of the integrated conservation equations. These profiles are used as starting conditions for an existing finite difference parabolic computer code for the turbulent supersonic combustion of hydrogen. Integrated mixing and flow profile results obtained from the computer code compare favorably with existing data for the supersonic combustion of hydrogen.
Document ID
19790035675
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Rogers, R. C. (NASA Langley Research Center High-Speed Aerodynamics Div., Hampton, Va., United States)
Date Acquired
August 9, 2013
Publication Date
January 1, 1979
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 79-0359
Meeting Information
Meeting: American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting
Location: New Orleans, LA
Start Date: January 15, 1979
End Date: January 17, 1979
Sponsors: American Institute of Aeronautics, Astronautics
Accession Number
79A19688
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.

Related Records

There are no records associated with this record.
No Preview Available