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Three-dimensional computations of transverse hydrogen jet combustion in a supersonic airstreamA computational fluid dynamics (CFD) code is being developed to compute the mixing and combustion of hydrogen fuel in the turbulent flow fields of supersonic combustion ramjets (scramjet). The code solves the three-dimensional Reynolds time-averaged complete Navier-Stokes equations including transport equations for a four species, two reaction, global finite rate chemistry model. The code was applied to the case of transverse injection of hydrogen from a sonic circular orifice into a supersonic airstream. The equations were numerically integrated using MacCormack's explicit method, and the algebraic eddy viscosity model of Baldwin-Lomax was used to model the turbulence. In the species transport and energy equations, diffusion coefficients based on Fick's Law and an assumption of unit Lewis number were applied. Computed features of the three-dimensional flow field are depicted by static pressure, static temperature, mass fraction of species, and velocity vectors. For engineering interest, mixing and combustion parameters were examined to assess the effect of injector diameter, injected fuel pressure, fuel-air ratio, and spacing of fuel injectors. The objective of the present paper is to demonstrate the capability of the present three-dimensional spatially elliptic, CFD code for turbulent, reacting flow. Application of the code to specific supersonic combustion configurations is planned.
Document ID
19870035134
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Uenishi, K.
(Vigyan Research Associates, Inc. Hampton, VA, United States)
Rogers, R. C.
(Vigyan Research Associates, Inc. Hampton, VA, United States)
Northam, G. B.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 13, 2013
Publication Date
January 1, 1987
Subject Category
Propellants And Fuels
Report/Patent Number
AIAA PAPER 87-0089
Accession Number
87A22408
Distribution Limits
Public
Copyright
Other

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