Preliminary Calibration of a Generic Scramjet Combustor

Abstract

The results of a preliminary investigation of the combustion of hydrogen fuel at hypersonic flow conditions are provided. The tests were performed in a generic, constant-area combustor model with test gas supplied by a free-piston-driven reflected-shock tunnel. Static pressure measurements along the combustor wall indicated that burning did occur for combustor inlet conditions of P(sub static) = approx. 19kPa, T(sub static) = approx. 1080K and velocity = approx. 3630 m/s with a fuel equivalence ratio = approx. 0.9. These inlet conditions were obtained by operating the tunnel with stagnation enthalpy H sub s 8.1 M J/kg , stagnation pressure P sub s = approx. 52MPa and a contoured nozzle with a nominal exit Mach number of 5.5.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1991
Accession Number
ADA234873

Entities

People

  • A. Paull
  • C. Brescianini
  • G. Kelly
  • M. Wendt
  • P. A. Jacobs
  • R. C. Rogers
  • R. G. Morgan

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Air Flow
  • Boundary Layer
  • Combustion
  • Computational Fluid Dynamics
  • Computer Programs
  • Engineering
  • Fluid Mechanics
  • Fuel Injection
  • Fuel Systems
  • Heat Transfer
  • Mach Number
  • Mechanical Engineering
  • Pressure Distribution
  • Pressure Measurement
  • Propulsion Systems
  • Shock Tubes
  • Shock Tunnels

Fields of Study

  • Physics

Readers

  • Combustion science or combustion engineering.
  • Fluid Dynamics.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow