Accession Number : AD0631649

Title :   EXPERIMENTAL INVESTIGATION OF THE SURFACE IMPACT PRESSURE PROBE METHOD OF MEASURING LOCAL SKIN FRICTION AT SUPERSONIC SPEEDS.

Descriptive Note : Master's thesis,

Corporate Author : DEFENSE RESEARCH LAB UNIV OF TEXAS AUSTIN

Personal Author(s) : Stalmach,Charles Joe ,Jr.

Report Date : JAN 1958

Pagination or Media Count : 124

Abstract : The purpose of the report is to demonstrate, on the basis of wind tunnel results, the feasibility of using a surface probe. This phase is limited to thermally insulated surfaces with zero pressure gradient.

Descriptors :   (*SKIN FRICTION, *SUPERSONIC FLIGHT), PRESSURE GAGES, PROBES, COMPRESSIBLE FLOW, WIND, EXPERIMENTAL DATA, PRESSURE, IMPACT SHOCK, SURFACE PROPERTIES, BOUNDARY LAYER

Subject Categories : Test Facilities, Equipment and Methods
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE