Accession Number : AD0657139

Title :   INTERFERENCE EFFECTS DUE TO RELATIVE PROXIMITY OF STATIC-PRESSURE PROBES IN SUPERSONIC FLOW,

Corporate Author : TEXAS UNIV AUSTIN DEFENSE RESEARCH LAB

Personal Author(s) : Lindsey,J. L.

Report Date : JUN 1957

Pagination or Media Count : 53

Abstract : An experimental investigation was conducted in a supersonic wind tunnel to determine the minimum critical spacing for no mutual interference of two cone-cylinder-type static-pressure probes designed for simultaneous pressure measurement in supersonic flow. Tests made over a Mach Number range of approximately 1.9 through 3.4 indicate that the minimum critical spacing is predominately a function of Mach Number and static-orifice location. Probe cone-angle and probe diameter variations produce minor effects. A theoretical study of static-orifice location was also made. Results indicate that the generally recommended position of six to ten probe diameters aft of the cone shoulder is suitable for pressure measurement at Mach Numbers as high as approximately 3.5; however, higher velocities require static-orifice locations at greater distances from the cone shoulder. (Author)

Descriptors :   (*PRESSURE GAGES, SUPERSONIC WIND TUNNELS), INTERFERENCE, STATICS, SUPERSONIC FLOW, ORIFICES

Subject Categories : Aerodynamics
      Test Facilities, Equipment and Methods
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE