THE DEVELOPMENT OF HIGH OUTPUT MINIATURIZED PRESSURE TRANSDUCERS FOR SHOCK TUNNEL TESTING.
Abstract
A description is presented of the developmental effort which culminated in the successful fabrication of two types of pressure transducers with performance suitable for use in the AF Aero Propulsion Laboratory 120-inch hypersonic shock tunnel. The one type transducer, intended primarily for use in sensing pitot pressure in the range from 0.1 to 100 psi, is one-eighth inch in diameter and two inches in length. The other type measures one-quarter inch in diameter and two-tenths inch in depth and is designed for sensing static or model pressures from 0.001 to 3 psi. Power amplifiers, integral with the transducer assemblies, are capable of driving up to 150 feet of shielded cable with normal capacitance of 30 pf per foot and achieving a time constant of 320 microseconds. Design details, fabricational techniques, calibration methods and calibration data, and shock tunnel test data and its correlation with the applicable theory as well as with other independent instrumentation are included. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1968
- Accession Number
- AD0830326
Entities
People
- Robert C. Macarthur
Organizations
- Calspan