Download or read book NOL Hypervelocity Wind Tunnel. Report No. 2: Nozzle Design written by and published by . This book was released on 1971 with total page 150 pages. Available in PDF, EPUB and Kindle. Book excerpt: The NOL hypervelocity wind tunnel will provide a high Reynolds number turbulent flow simulation in the Mach number range 10 to 20. This facility, much needed for large-scale testing of hypersonic vehicles, will be operational late in 1972. This report presents the detailed procedure used to design three nozzles for the facility. Pressure and temperature effects on the thermodynamic properties of nitrogen are taken into account in both the inviscid core and the boundary layer calculations. The supersonic portion of the inviscid core is calculated by the method of characteristics and the subsonic portion is approximated as a one-dimensional flow. The boundary layer calculation procedure is based on an integral moment of momentum equation and is valid for thick as well as thin boundary layers.