Accession Number:

ADA214917

Title:

Combustor/Inlet Interactions and Modeling of Hypersonic Dual Combustion Ramjet Engines

Descriptive Note:

Final rept. 1 Oct 1982-30 Sep 1983

Corporate Author:

JOHNS HOPKINS UNIV LAUREL MD APPLIED PHYSICS LAB

Personal Author(s):

Report Date:

1983-05-10

Pagination or Media Count:

22.0

Abstract:

Two distinct but related basic research efforts are being investigated under the joint sponsorship of the U.S. Air Force Office of Scientific Research AFOSR and the U.S. Naval Sea Systems Command NAVSEA. The first effort is to experimentally characterize the flowfields at the entrance of supersonic combustors in hypersonic dual-combustion ramjet engines and the second is to develop the component and engine cycle analysis required to predict the internal flowfields and performance of these engines. Both are basic to the successful development of advanced, hypersonic airbreathing engines. Progress to date includes the development of a simplified axisymmetric mixing and combustion analysis and a concomitant wall boundary layer analysis which describe the major flow phenomena within the main supersonic combustor of a dual combustion ramjet engine. The experimental hardware for the combustorinlet interaction tests is also complete and initial testing has begun. Currently, refinements to the combustion and wall boundary layer analysis with particular emphasis on the base flowmixing region, are being pursued and testing with the combustorinlet interaction hardware continue. kt

Subject Categories:

  • Combustion and Ignition
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE