Accession Number : AD0429312


Title :   FILM COOLING IN SUPERSONIC FLOW,


Descriptive Note : Technical rept.,


Corporate Author : MINNESOTA UNIV MINNEAPOLIS HEAT TRANSFER LAB


Personal Author(s) : Goldstein, R J ; Tsou, F K


Report Date : Dec 1963


Pagination or Media Count : 1


Abstract : The effect of injecting a secondary gas stream at a rearward facing slot into a supersonic air flow was examined. A small Mach 3 wind tunnel was constructed and initially tested with no step present. A slot permitting injection of a secondary gas, parallel to the main air flow, at the wall was then installed. The step height is 0.121 in. with a slot opening of 0.064 in. The secondary gas can be heated and its flow rate varied. Air is the secondary fluid used in the experiments described herein. The absolute injection temperature is between 1.04 and 1.20 of the primary stream total temperature. The ratio, M, of the mass velocity in the secondary stream to that in the primary stream is in the range from zero to 0.16, corresponding to a maximum Mach number of 0.95. Schlieren photographs are presented and static wall pressure and adiabatic wall temperature measurements are described. The film cooling effectiveness is found to stay close to the value one for a distance of approximately 8 slot heights and to fall off rapidly downstream from this point. (Author)


Descriptors :   *FILM COOLING , SUPERSONIC FLOW , TEMPERATURE , AIR , HEATING , WIND TUNNELS , INJECTION , VELOCITY , ORIFICES


Distribution Statement : APPROVED FOR PUBLIC RELEASE