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) : Chambers,Harold F.

Report Date : OCT 1966

Pagination or Media Count : 40

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)

Descriptors :   (*SUPERSONIC COMBUSTION, SIMULATION), (*SUPERSONIC COMBUSTION RAMJET ENGINES, MODEL TESTS), WIND TUNNELS, NOZZLES, ENGINE AIR SYSTEMS COMPONENTS, SHOCK TUBES, MATHEMATICAL ANALYSIS

Subject Categories : Test Facilities, Equipment and Methods
      Combustion and Ignition
      Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE