ANALYTICAL STUDY OF SHOCK TUNNEL SIMULATION OF COMBUSTOR ENTRANCE CONDITIONS,
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1966
- Accession Number
- AD0646599
Entities
People
- Harold F. Chambers
Organizations
- Air Force Research Laboratory