Numerical simulations of atlas II rocket motor plumes

Ram M. Rao, Krishnendu Sinha, Graham V. Candler, Michael J. Wright, Deborah A. Levin

Research output: Contribution to conferencePaperpeer-review

8 Scopus citations

Abstract

Previous numerical simulations of Atlas rocket plumes showed poor agreement with experimental radiation data. It was proposed that the lack of agreement is partly due to inadequate grid resolution, disregarding turbulence effects and the absence of any modeling of soot which is present in the flow. In the present work two of these issues are addressed by using a higher order numerical scheme to overcome the computational grid size requirements and a two-equation turbulence model to address the effects of turbulence. A parametric study conducted on an axisymmetric plume for various initial values of turbulent kinetic energy, k, and turbulent dissipation rate, ϵ, indicates that there are upper and lower limits to the values of these parameters to sustain turbulence in the flow. In all above cases, an increase in temperature is seen in the shear layer and as a consequence a significantly higher number density of OH is observed. Higher OH number density is expected to result in increased radiance in the UV spectrum. A grid resolution study for a fixed k and ϵ case indicates that there is an increase in the turbulence level as the grid is refined. A laminar run with inflow energy level equivalent to one of the turbulent cases indicates an increase in temperature in the shear layer which is comparable to that in the turbulent case, and consequently higher OH number densities. Also increasing initial turbulent kinetic energy resulted in higher temperature even when turbulence was not sustained by the flow. Hence the flow energetics may play an important role in determining the flow physics and species concentrations. The results obtained from the axisymmetric parametric study are used to determine the parameters needed for the turbulence model in the 3D computations. A third order accurate MUSCL Steger-Warming scheme with the k-ϵ turbulence model is used compute the three-dimensional Atlas II flow solutions. This turbulent solution shows higher temperature and OH number density in the shear layer.

Original languageEnglish (US)
StatePublished - 1999
Event35th Joint Propulsion Conference and Exhibit, 1999 - Los Angeles, United States
Duration: Jun 20 1999Jun 24 1999

Other

Other35th Joint Propulsion Conference and Exhibit, 1999
Country/TerritoryUnited States
CityLos Angeles
Period6/20/996/24/99

Bibliographical note

Funding Information:
The first three authors were supported by the Army Research Office under grant number DAAG55-97-1-0406. Research performed at GWU is based upon work supported by the U.S. Army Research Office under grant number DAAG55-98-1-009. This work was also supported in part by the U.S. Army High Performance Computing Research Center under the auspices of the Department of the Army, Army Research Laboratory cooperative agreement number DAAH04-95-2-0003 / contract number DAAH04-95-C-0008, the content of which does not necessarily reflect the position or the policy of the government, and no official endorsement should be inferred.

Publisher Copyright:
© 1999 by Ram M. Rao. Published by the American Institute of Aeronautics and Astronautics, Inc.

Fingerprint

Dive into the research topics of 'Numerical simulations of atlas II rocket motor plumes'. Together they form a unique fingerprint.

Cite this