Accession Number : AD0826149

Title :   USE OF A PULSE HEATED FINE WIRE PROBE FOR THE MEASUREMENT OF TOTAL TEMPERATURE IN SHOCK DRIVEN FACILITIES.

Descriptive Note : Technical information series,

Corporate Author : GENERAL ELECTRIC CO PHILADELPHIA PA MISSILE AND SPACE DIV

Personal Author(s) : Softley, E. J.

Report Date : FEB 1968

Pagination or Media Count : 44

Abstract : A fine wire placed in a flow stream will experience an energy transfer rate dependent on various flow properties and on the difference between a wire recovery temperature T sub R and the wire temperature T sub w. By applying an electrical pulse T sub w can be varied during the flow duration, and from measurements made on the wire the value of T sub R (or its subsequent history if it is time dependent) can be determined. The stagnation temperature approximates the quantity T sub R and can be determined directly from it in many applications. Measurements behind an incident shock in a shock tube has resulted in measurements of T sub s to within 5% of that calculated from shock velocity. Applications of the technique to hypersonic near wakes and to boundary layers undergoing transition are demonstrated. (Author)

Descriptors :   *TEMPERATURE SENSITIVE ELEMENTS), (*REENTRY VEHICLES, WAKE), (*SHOCK TUBES, PROBES), (*PROBES, WIRE, TEMPERATURE, MEASUREMENT, GAS FLOW, STAGNATION POINT, HYPERSONIC CHARACTERISTICS, TEST METHODS, BOUNDARY LAYER TRANSITION, ATMOSPHERE ENTRY, SIMULATION.

Subject Categories : Test Facilities, Equipment and Methods
      Fluid Mechanics
      Unmanned Spacecraft

Distribution Statement : APPROVED FOR PUBLIC RELEASE