An asymptotic plume growth method based on a time-accurate three-dimensional computational fluid dynamics formulation has been developed to assess the exhaust-plume pollutant environment from a simulated RD-170 engine hot-fire test on the F1 Test Stand at Marshall Space Flight Center. Researchers have long known that rocket-engine hot firing has the potential for forming thermal nitric oxides, as well as producing carbon monoxide when hydrocarbon fuels are used. Because of the complex physics involved, moot attempts to predict the pollutant emissions from ground-based engine testing have used simplified methods, which may grossly underpredict and/or overpredict the pollutant formations in a test environment. The objective of this work has been to develop a computational fluid dynamics-based methodology that replicates the underlying test-stand flow physics to accurately and efficiently assesses pollutant emissions from ground-based rocket-engine testing. A nominal RD-170 engine hot-fire test was computed, and pertinent test-stand flow physics was captured. The predicted total emission rates compared reasonably well with those of the existing hydrocarbon engine hot-firing test data. l,u, v. w, H,k,e, or_ti = residue term for q equation = source term for q equation = static temperature = transformed velocity, (contravariant velocity) x volume = mean velocities in x, y, and z directions = physical coordinates = mass fraction for species i = difference operator, Aqi + i/2 : qi + 1 --qi = turbulent kinetic energy dissipation rate = effective viscosity = turbulent eddy viscosity = computational coordinates = density = energy dissipation function, pG = mass production rate for species i
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