An analysis of artificial viscosity effects on reacting flows using a spectral multi-domain techniqueAnalytical and experimental techniques for modeling the aerothermodynamics of hypersonic flight are assessed, together with the problems which will be encountered in developing reusable hypersonic vehicles. Emphasis is placed on a numerical coupling between a nonequilibrium chemistry model and hypersonic flow kinematics. Finite difference and finite element descriptions of flow fields in which molecules encounter a shock wave and undergo various motion (and thereby energy) transformations are discussed. The effects of artificial smearing of the shock wave are considered in terms of the resulting effects on the distribution of the energies and chemical composition of the transition region. Results are provided from schlieren photographs of shock-tube experiments, Navier-Stokes calculations of axisymmetric flow over a conical body, and calculations using a spectral multidomain approach for chemically reacting flows.
Document ID
19880023722
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Macaraeg, Michele G. (NASA Langley Research Center Hampton, VA, United States)
Streett, Craig L. (NASA Langley Research Center Hampton, VA, United States)