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Numerical simulation of hypersonic inlet flows with equilibrium or finite rate chemistryAn efficient numerical program incorporated with comprehensive high temperature gas property models has been developed to simulate hypersonic inlet flows. The computer program employs an implicit lower-upper time marching scheme to solve the two-dimensional Navier-Stokes equations with variable thermodynamic and transport properties. Both finite-rate and local-equilibrium approaches are adopted in the chemical reaction model for dissociation and ionization of the inlet air. In the finite rate approach, eleven species equations coupled with fluid dynamic equations are solved simultaneously. In the local-equilibrium approach, instead of solving species equations, an efficient chemical equilibrium package has been developed and incorporated into the flow code to obtain chemical compositions directly. Gas properties for the reaction products species are calculated by methods of statistical mechanics and fit to a polynomial form for C(p). In the present study, since the chemical reaction time is comparable to the flow residence time, the local-equilibrium model underpredicts the temperature in the shock layer. Significant differences of predicted chemical compositions in shock layer between finite rate and local-equilibrium approaches have been observed.
Document ID
19880040490
Document Type
Conference Paper
Authors
Yu, Sheng-Tao (NASA Lewis Research Center Cleveland, OH, United States)
Hsieh, Kwang-Chung (NASA Lewis Research Center Cleveland, OH, United States)
Shuen, Jian-Shun (NASA Lewis Research Center; Sverdrup Technology, Inc. Cleveland, OH, United States)
Mcbride, Bonnie J. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 13, 2013
Publication Date
January 1, 1988
Subject Category
AERODYNAMICS
Report/Patent Number
AIAA PAPER 88-0273
Distribution Limits
Public
Copyright
Other