Accession Number:

AD0646599

Title:

ANALYTICAL STUDY OF SHOCK TUNNEL SIMULATION OF COMBUSTOR ENTRANCE CONDITIONS,

Descriptive Note:

Master's thesis,

Corporate Author:

AIR FORCE AERO PROPULSION LAB WRIGHT-PATTERSON AFB OHIO

Personal Author(s):

Report Date:

1966-10-01

Pagination or Media Count:

40.0

Abstract:

In order to study the simulation capability of the shock tunnel, a set of combustor entrance conditions was generated from a 10-degree, two-shock wedge inlet and a trajectory of 1250 psf. These were compared with shock tunnel calculations for a 15-degree half-angle conical nozzle, a 5-degree half-angle conical nozzle, and a 5-degree 2-dimensional nozzle. The matching of pressure, temperature, velocity, and composition was studied. The composition deviation in the shock-tunnel nozzle was examined for its effect on hydrogen combustion ignition delay time. Author

Subject Categories:

  • Test Facilities, Equipment and Methods
  • Combustion and Ignition
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE