Accession Number:

AD0466354

Title:

FLOW STUDIES IN A CONTOURED NOZZLE DESIGNED FOR A SMALL HELIUM HYPERSONIC WIND TUNNEL.

Descriptive Note:

Technical memo.,

Corporate Author:

JOHNS HOPKINS UNIV LAUREL MD APPLIED PHYSICS LAB

Personal Author(s):

• Mark, F. F.

Report Date:

1965-04-01

Pagination or Media Count:

40.0

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

Descriptors:

• *WIND TUNNEL NOZZLES
• *HYPERSONIC WIND TUNNELS
• WIND TUNNEL NOZZLES
• PRESSURE
• HELIUM
• HYPERSONIC NOZZLES
• BOUNDARY LAYER
• HYPERSONIC FLOW
• LAMINAR BOUNDARY LAYER
• PITOT TUBES
• PRESSURE GAGES
• INSTRUMENTATION
• HYPERSONIC CHARACTERISTICS
• SUPERSONIC CHARACTERISTICS

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE