DSMC Study of Flowfield and Kinetic Effects on Vibrational Excitations in Jet-Freestream Interactions

Abstract

Vibrational excitation of molecular species emitting from a jet into a high-speed free stream is a process with importance to the prediction of high-altitude rocket exhaust plume infrared emissions. Accurate predictions of these emissions are necessary for the analysis of potential optical interference of on-vehicle instrumentation. Unfortunately, accurate vibrational excitation collision cross sections are not always available for the species pairs of interest and for the high relative energies encountered in this situation. In addition, accurate nozzle exit plane flowfield characteristics are always a challenge to calculate accurately. The results of a study to characterize the sensitivity of predicted vibrational excitation to the vibrational excitation cross section and the nozzle exit plane profile will be presented in this paper. The Direct Simulation Monte Carlo (DSMC) computational technique was used to simulate the interaction between a carbon monoxide jet and a high velocity free steam of oxygen atoms oriented at 900 degrees to the jet flow axis at 150 kilometers simulated altitude. A literature value of the vibrational excitation cross section is used as a baseline, and comparative simulations are made for cross sections that vary around that value. Similarly, the nozzle exit plane profile is varied from a "flat" profile to a fully developed laminar boundary layer profile to obtain sensitivities to the jet inflow startline. SMILE, a software system based on the DSMC method, developed at the Institute of Theoretical and Applied Mechanics, Novosibirsk, Russia, has been utilized for this study. This code is capable of fully 3-D parallel calculations, and has a graphical user interface, xSMILE, that automates the process of setting up a case, running the main SMILE code, and obtaining output in a useable form.

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Document Details

Document Type
Technical Report
Publication Date
May 15, 2002
Accession Number
ADA410985

Entities

People

  • David H. Campbell

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Air Force Research Laboratories
  • Applied Mechanics
  • Boundary Layer
  • Carbon Monoxide
  • Dielectric Gases
  • Excitation
  • Exhaust Plumes
  • Gas Dynamics
  • Graphical User Interface
  • High Altitude
  • Jet Flow
  • Laminar Boundary Layer
  • Mechanics
  • Military Research
  • Monte Carlo Method
  • User Interface

Fields of Study

  • Physics

Readers

  • Aerospace Propulsion Engineering.
  • Combustion and Flow Dynamics.
  • Spectroscopy.