Accession Number : AD0475736

Title :   SUBSONIC TESTS IN FREE MOLECULE FLOW ON IMPACT TUBE PRESSURE PROBES HAVING A WIDE RANGE OF TUBE LENGTHS AT ANGLES OF ATTACK UP TO 90 DEGREES.

Descriptive Note : Technical note,

Corporate Author : TORONTO UNIV DOWNSVIEW (ONTARIO) INST FOR AEROSPACE STUDIES

Personal Author(s) : Hughes, P. C.

Report Date : JUN 1965

Pagination or Media Count : 60

Abstract : Subsonic tests were performed in the UTIAS low density wind tunnel to obtain data on the free molecule properties of impact tube pressure probes at subsonic speeds over a wide range of tube lengths. The data substantiated recent theoretical calculations. For non-zero angles of attack it was found that the probe pressure ratio can be approximated by assuming that the probe is at zero angle of attack to the axial component of the speed ratio. This approximation will yield a value which is too high and will be more in error as either the speed ratio or the impact tube length/diameter ratio is increased. (Author)

Descriptors :   (*SHOCK TUBES, PRESSURE GAGES), SUBSONIC FLOW, PROBES, HYPERSONIC FLOW, WIND TUNNEL NOZZLES, MOLECULAR PROPERTIES, RAREFIED GAS DYNAMICS, MOLECULAR STRUCTURE, ANGLE OF ATTACK, MEASURING INSTRUMENTS, INSTRUMENTATION, WIND TUNNELS, CALIBRATION, TRANSDUCERS, IMPACT SHOCK, MATHEMATICAL ANALYSIS, EXPERIMENTAL DATA, ERRORS.

Subject Categories : Test Facilities, Equipment and Methods
      Recording and Playback Devices
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE