Design and Calibration of a Total-Temperature Probe for Use at Supersonic Speeds
Abstract
The results of a study of the factors involved in the design of total-temperature probes for use at supersonic speeds have been applied to the design of an instrument to be used in wind-tunnel calibrations. Tests of the probe showed that the calibration factor required in the conversion of the measured temperature to the true total temperature was 0.992 +/- 0.002 for a range of Mach numbers between 1.36 and 2.01. The calibration factor was insensitive to angles of inclination relative to the air stream up to 30 for the range of Mach numbers from 1.36 to 2.01, and up to 90 at a Mach number of 1.50. These values of angle of inclination and Mach number were the limits of the range of test conditions for the investigation.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1949
- Accession Number
- ADA380572
Entities
People
- David L. Goldstein
- Richard Scherrer
Organizations
- University of Southern California