Three-dimensional calculations of supersonic reacting flows using an LU scheme

doi:10.1016/0021-9991(92)90005-J

Journal of Computational Physics

Volume 101, Issue 2, August 1992, Pages 276-286

https://doi.org/10.1016/0021-9991(92)90005-J Get rights and content

Abstract

A new three-dimensional numerical program that incorporates comprehensive real gas property models has been developed to simulate supersonic reacting flows. The code employs an implicit, finite volume, Lower-Upper (LU), time-marching method to solve the complete Navier-Stokes and species equations in a fully coupled and very efficient manner. A chemistry model with nine species and eighteen reaction steps is adopted in the program to represent the chemical reactions of H₂ an air. To demonstrate the capability of the program, flow fields of underexpanded hydrogen jets transversely injected into the supersonic airstream inside the combustors of scramjets are calculated. Results clearly depict the flow characteristics, including the shock structure, the separated flow regions around the injector, and the distribution of the combustion products.

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Three-dimensional calculations of supersonic reacting flows using an LU scheme

Abstract

J. Comput. Phys.

AIAA J.

AIAA J.

Numerical Simulation of Hypersonic Inlet Flows with Equilibrium or Finite Rate Chemistry

AIAA Paper 88-0273

A Laser-Induced Fluorescence Visualization Study of Transverse, Sonic Fuel Injection in a Nonreacting Supersonic Combustor

AIAA Paper 86-0570

Combustion Theory

Combustion Theory

Computer Program for the Calculation of Complex Equilibrium Compositions, Rocket Performance, Incident and Reflected Shocks, and Chapman-Jouguet Detonations

NASA SP-273