Thermal Performance of a Scramjet Combustor Operating at Mach 5.6 Flight Conditions.

Abstract

This report describes the experimental data and the procedures used in acquiring and reducing the thermal loads data during tests of a hydrocarbon-fueled scramjet combustor at United Technologies Research Center (UTRC). This research effort is part of the UTRC effort to develop dual-mode scramjet combustor technology to support the development of Mach S missile technology. The objective of the thermal loads testing was to map the thermal and mechanical loads, including heat transfer, dynamic and static pressures, and skin friction in a scramjet combustor during direct-connect scramjet tests. The tests were conducted at the UTRC Ramject/Scramjet direct-connect combustor test facility in East Hartford, CT.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1997
Accession Number
ADA353103

Entities

People

  • Deems S. Emmer
  • Richard D. Neumann
  • Scott Stouffer

Organizations

  • University of Dayton

Tags

Communities of Interest

  • Advanced Electronics
  • Sensors
  • Weapons Technologies

DTIC Thesaurus Topics

  • Combustion
  • Combustors
  • Computational Fluid Dynamics
  • Data Acquisition
  • Engines
  • Fluid Flow
  • Fuel Injectors
  • Heat Transfer
  • Ignition Lag
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Skin Friction
  • Strain Gages
  • Supersonic Combustion Ramjet Engines
  • Test Facilities
  • Thermal Conductivity

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Internal Combustion Engine (ICE) Technology.