Accession Number : AD0018796


Title :   MEASUREMENTS OF PRESSURE DISTRIBUTION AND BOUNDARY-LAYER TRANSITION ON A HOLLOW-CYLINDER MODEL


Corporate Author : NAVAL ORDNANCE LAB WHITE OAK MD


Personal Author(s) : Lee, Roland E


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/018796.pdf


Report Date : 28 Apr 1953


Pagination or Media Count : 28


Abstract : Measurements were made on a 4-in.-od hollow-cylinder model with its center line adjusted parallel to the flow in the NOL 40 x 40-cm Aeroballistics Intermittent Wind Tunnel no. 2 at 6 Mach numbers between 2.2 and 5.0. At these Mach numbers, supersonic flow was attained inside the cylinder. Pressure distributions on the hollow cylinder were nearly the same as the free-stream static pressure distribution. The location of boundary-layer transition was determined from schlieren photographs. The transition Reynolds numbers for the hollow cylinder decreased with increasing Mach number. The results of the boundary-layer transition were compared with those obtained previously on a 5 deg cone and a 20 deg cone-cylinder in the same tunnel.


Descriptors :   *BOUNDARY LAYER TRANSITION , *WIND TUNNEL MODELS , *PRESSURE DISTRIBUTION , MACH NUMBER , PARALLEL ORIENTATION , SUPERSONIC FLOW , SCHLIEREN PHOTOGRAPHY , CYLINDRICAL BODIES , STATIC PRESSURE , REYNOLDS NUMBER , FLOW , TRANSITIONS , FREE STREAM


Subject Categories : Fluid Mechanics


Distribution Statement : APPROVED FOR PUBLIC RELEASE