A Comparison of Computational Fluid Dynamics Computer Programs for Hypersonic Propulsive Nozzle Flowfields
Abstract
This study compared the results of two computer programs, a flux- difference-splitting (FDS) Godunov-based scheme and the SCPAMjet Hypersonic Nozzle (SCHNOZ) paraobolized Navier-Stoke's code using MacCormack's method, applied to a hypersonic nozzle flowfield. Two different nozzle geometries were investigated at three Mach numbers along a typical hypersonic flight trajectory. A direct compariosn between the SCHNOZ and FDS programs was made by numerically solving the steady Euler equations using a frozen flow assumption in the nozzle. The frozen flow SCHNOZ code is currently 6 to 10 times more efficient in terms of computational time than the FDS frozen flow code. The SCHNOZ and FDS codes demonstrated comparable accuracy in modeling the flow physics. The implementation of the viscous terms in the SCHNOZ code proved to be ineffectual in modeling the viscous effects in the flowfield. The finite rate chemistry effects were important for the nozzle inlet conditions considered.... Hypersonic nozzle, SCRAMjet, NASP, Riemann problem, Flux-Difference-Splitting, Thermodynamic, Model, Hypersonic propulsion.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1992
- Accession Number
- ADA259146
Entities
People
- Kennedy B. Wilson Jr
Organizations
- Air Force Institute of Technology