Predictions of a Supersonic Jet-in-Crossflow: Comparisons Among CFD Solvers and with Experiment

Abstract

A supersonic jet interaction flowfield with pressure ratios of 2.8-16.7 exhausting into subsonic and transonic crossflows (Mach 0.5-0.8) was simulated using computational fluid dynamics and compared to experimental particle image velocimetry data. Three independent studies using different Reynolds-averaged Navier-Stokes flow solvers and a variety of turbulence models were used to assess the accuracy level of the predicted downstream flow physics of the jet interaction problem. Evaluation of the prediction of the downstream flow structure was made via comparisons of the three components of velocity and turbulent kinetic energy. In general, the predicted jet interaction flowfield was highly sensitive to the turbulence model used, with performance of the turbulence model being dependent on the flow solver, and relatively insensitive to crossflow Mach number in the range investigated.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Sep 01, 2014
Accession Number
ADA614008

Entities

People

  • Clark D. Mikkelsen
  • James DeSpirito
  • Kevin D. Kennedy
  • Ross A. Chaplin

Organizations

  • United States Army Research Laboratory

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Accuracy
  • Air Force
  • Boundary Layer
  • Computational Fluid Dynamics
  • Dynamics
  • Flow
  • Fluid Dynamics
  • Fluid Flow
  • Mach Number
  • Military Research
  • Pressure Distribution
  • Pressure Measurement
  • Test And Evaluation
  • Three Dimensional
  • Turbulence
  • Turbulent Mixing
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics