FLOW STUDIES IN A CONTOURED NOZZLE DESIGNED FOR A SMALL HELIUM HYPERSONIC WIND TUNNEL.
Abstract
Pressure measurements were made in a contoured nozzle designed for a 2 in. Helium Hypersonic Wind Tunnel. This nozzle was designed to give a uniform Mach 18 flow at the test section. The investigation showed that the measured exit centerline Mach number was less than the design value and that a nonuniform flow existed in this region. These results were attributed to the boundary layer displacement thickness being considerably larger than estimated. Uniform Mach 14.7 flow was produced at a station about onethird of the nozzle length from the exit. The flow characteristics of this nozzle provide a basis for the evaluation of the techniques of estimating the viscous flow correction in small contoured nozzle. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1965
- Accession Number
- AD0466354
Entities
People
- F. F. Mark
Organizations
- Johns Hopkins University