Disturbances from Shock/Boundary-Layer Interactions Affecting Upstream Hypersonic Flow

Abstract

Large disturbances and decreased Mach number in the core flow were sometimes found in the downstream end of the nozzle of the Boeing/AFOSR Mach-6 Ludwieg Tube at Purdue University. The cause of the disturbances has been identified using Kulite pressure transducer, hot wire, and hot film measurements. These disturbances were found to be separations caused by shock/boundary-layer interactions in the diffuser, often originating from shocks generated at the sting support. Some disturbances were found to propagate upstream about 100 boundary layer thicknesses. The large upstream effect is due to the laminar boundary layers being very susceptible to separation. Attempts to prevent the separations from propagating upstream included an improved sting mount, compression rings to thin the boundary layer, and trip rings to trip the boundary layer. These attempts were not successful. A diffuser section with an increased area is proposed to prevent the separations from propagating upstream.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Dec 01, 2005
Accession Number
ADA441155

Entities

People

  • Craig R. Skoch

Organizations

  • Purdue University

Tags

Communities of Interest

  • Air Platforms
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerospaceplanes
  • Bleed Systems
  • Boundary Layer
  • Boundary Layer Transition
  • Fabrication
  • Fluid Dynamics
  • Hypersonic Flow
  • Hypersonic Vehicles
  • Measurement
  • Noise
  • Pressure Gradients
  • Reentry Vehicles
  • Research Facilities
  • Supersonic Combustion Ramjet Engines
  • Theses
  • Tubes
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Fluid Dynamics.
  • Plasma Physics / Magnetohydrodynamics

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow