Accession Number : AD0263572

Title :   MEASUREMENT OF FLOW ANGULARITY AT SUPERSONIC AND HYPERSONIC SPEEDS WITH THE USE OF A CONICAL PROBE

Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON D C

Personal Author(s) : SWALLEY,FRANK E.

Report Date : SEP 1961

Pagination or Media Count : 1

Abstract : The characteristics of a 40 degrees half-angle cone for measuring flow angularity were determined experimentally. Tests were conducted at a Mach number of 21 in helium with check points at Mach number 3.55 in air for angles of pitch up to 5 degrees. The air tests confirmed theoretical indications of small or negligible Mach number and test-medium effects for the case of air and helium. The instrument is capable of measuring flow angularity at high Reynolds numbers and speeds greater than that necessary for shock attachment to within + or - 1/3-degrees. (Author)

Descriptors :   *CONICAL BODIES, *CYLINDRICAL BODIES, *HYPERSONIC FLOW, FLIGHT SPEEDS, FLIGHT TESTING, HYPERSONIC CHARACTERISTICS, HYPERSONIC WIND TUNNELS, MEASUREMENT, MODEL TESTS, PRESSURE, SUPERSONIC FLOW, WIND TUNNEL MODELS

Distribution Statement : APPROVED FOR PUBLIC RELEASE