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Hypersonic Combustor Model Inlet CFD Simulations and Experimental ComparisonsNumerous two-and three-dimensional computational simulations were performed for the inlet associated with the combustor model for the hypersonic propulsion experiment in the NASA Ames 16-Inch Shock Tunnel. The inlet was designed to produce a combustor-inlet flow that is nearly two-dimensional and of sufficient mass flow rate for large scale combustor testing. The three-dimensional simulations demonstrated that the inlet design met all the design objectives and that the inlet produced a very nearly two-dimensional combustor inflow profile. Numerous two-dimensional simulations were performed with various levels of approximations such as in the choice of chemical and physical models, as well as numerical approximations. Parametric studies were conducted to better understand and to characterize the inlet flow. Results from the two-and three-dimensional simulations were used to predict the mass flux entering the combustor and a mass flux correlation as a function of facility stagnation pressure was developed. Surface heat flux and pressure measurements were compared with the computed results and good agreement was found. The computational simulations helped determine the inlet low characteristics in the high enthalpy environment, the important parameters that affect the combustor-inlet flow, and the sensitivity of the inlet flow to various modeling assumptions.
Document ID
Document Type
Preprint (Draft being sent to journal)
Venkatapathy, E. (Thermoscience Inst. Moffett Field, CA United States)
TokarcikPolsky, S. (Sterling Software, Inc. Palo Alto, CA United States)
Deiwert, G. S. (NASA Ames Research Center Moffett Field, CA United States)
Edwards, Thomas A.
Date Acquired
August 20, 2013
Publication Date
January 1, 1995
Subject Category
Fluid Mechanics and Thermodynamics
Funding Number(s)
PROJECT: RTOP 505-70-62
Distribution Limits
Work of the US Gov. Public Use Permitted.