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):
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