Accession Number:

AD0657133

Title:

THE MACH NUMBER AND TEMPERATURE CALIBRATION OF AN AXISYMMETRIC, INTERMITTENT-FLOW SUPERSONIC WIND TUNNEL,

Descriptive Note:

Corporate Author:

TEXAS UNIV AUSTIN DEFENSE RESEARCH LAB

Personal Author(s):

Report Date:

1957-06-01

Pagination or Media Count:

61.0

Abstract:

Static pressure and temperature surveys were conducted in the 4.5-inch diameter, axisymmetric, intermittent-flow, supersonic wind tunnel to determine the flow characteristics. Both horizontal and vertical surveys were made at nine stations along the center line one inch apart. The static pressures were measured using Statham pressure transducers. The maximum Mach number variation was plus or minus 0.02 for the upstream part of the test section and plus or minus 0.03 for the downstream part. An axial Mach number gradient of 0.012 per inch was found. There was no evidence of a focussing conical shock wave in the core of the test section. A five-probe, shielded-thermocouple type, temperature rake measured stagnation temperatures in the test section. The maximum temperature variation across the test section was 0.66 percent of the absolute stagnation temperature. Author

Subject Categories:

  • Test Facilities, Equipment and Methods

Distribution Statement:

APPROVED FOR PUBLIC RELEASE