Accession Number : AD0463276


Title :   THE AERODYNAMIC DESIGN OF AXISYMMETRIC NOZZLES FOR HIGH-TEMPERATURE AIR,


Corporate Author : NAVAL ORDNANCE LAB WHITE OAK MD


Personal Author(s) : Enkenhus, K R ; Maher, E F


Report Date : 05 Feb 1962


Pagination or Media Count : 71


Abstract : A method is given for aerodynamic design of contoured axisymmetric nozzles by the method of characteristics, with a turbulent boundarylayer correction, for high-temperature air in thermodynamic equilibrium. The method has been coded on an IBM 704 computer, and used to investigate boundary-layer growth and heat transfer in a family of hypervelocity nozzles having exit Mach numbers from 11 to 19, supply pressures from 50 to 500 atmospheres and supply temperatues up to 7500 K. (Author)


Descriptors :   *WIND TUNNEL NOZZLES , AIR , WIND TUNNELS , SCIENTIFIC RESEARCH , SHOCK TUBES , AXISYMMETRIC FLOW


Distribution Statement : APPROVED FOR PUBLIC RELEASE