Improved Simulation of Inflow Distortion for Direct-Connect Scramjet Studies

Abstract

A technique to develop flight-like inflow conditions for direct-connect testing has been extended in the current work. This technique utilizes an expansion/contraction section upstream of the engine isolator in a direct-connect test facility to create shock waves consistent with those generated in flight. The current work improves upon the earlier work by better matching the inlet shock structures, the average conditions at the engine throat, and boundary layer properties. RANS CFD simulations have been performed for isolators downstream of a flight inlet, a direct-connect facility nozzle without distortion, and a direct-connect facility nozzle with distortion. The RANS CFD simulations predict similar shock positions in all cases, however a change in the mass flux distribution at the exit plane is observed.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Apr 01, 2011
Accession Number
ADA543745

Entities

People

  • Dean R. Eklund
  • Mark Hagenmaier
  • Ryan T. Milligan

Organizations

  • Air Force Research Laboratory

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Air Force
  • Air Force Research Laboratories
  • Boundaries
  • Boundary Layer
  • Computational Fluid Dynamics
  • Distortion
  • Fluid Dynamics
  • Fluid Flow
  • Generators
  • Layers
  • Mach Number
  • Mechanical Properties
  • Pressure Distribution
  • Shear Stresses
  • Simulations
  • Test Facilities

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Computational Fluid Dynamics (CFD)