Accession Number : AD0708475

Title :   CONDENSATION IN A CONTOURED-NOZZLE SHOCK TUNNEL,

Descriptive Note : Rept. for Jan-Apr 70,

Corporate Author : AEROSPACE CORP EL SEGUNDO CALIF LAB OPERATIONS

Personal Author(s) : Varwig,Robert L. ; Mason,Stephen B.

Report Date : 01 JUL 1970

Pagination or Media Count : 27

Abstract : The onset of condensation in a hypersonic shock tunnel was investigated to determine the limiting temperature to which the gas may be expanded. Previous research indicated some supercooling could be obtained; however, a confident assessment could not be made because of scatter in available experimental results. Static wall pressure and pitot pressure, which vary with condensation, were measured, while reservoir temperature was reduced for constant reservoir pressure. Under these conditions, measurements were made of condensation and supercooling. (Author)

Descriptors :   (*SHOCK TUBES, SUPERSONIC NOZZLES), (*CONDENSATION, NOZZLE GAS FLOW), REYNOLDS NUMBER, SUPERCOOLING, PRESSURE, TEMPERATURE, TEST FACILITIES, INSTRUMENTATION, DATA PROCESSING, HYPERSONIC WIND TUNNELS

Subject Categories : Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE