Accession Number : AD0015004


Title :   MEASUREMENT OF BOUNDARY-LAYER TRANSITION ON A STANDARD MODEL TO DETERMINE THE RELATIVE DISTURBANCE LEVEL IN TWO SUPERSONIC WIND TUNNELS


Corporate Author : NAVAL ORDNANCE LAB WHITE OAK MD


Personal Author(s) : Lange, A H ; Gieseler, L P


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/015004.pdf


Report Date : 19 Feb 1953


Pagination or Media Count : 28


Abstract : The boundary-layer transition on a slender cone was observed for 1.9 less than or equal to M less than or equal to 4.2 in 2 supersonic wind tunnels. A 5 total apex angle cone, 50 cm long and 4.5 cm in diameter at the base, was used as a standard. The transition in the boundary layer was determined by a luminescent lacquer technique and by spark-schlieren photography. The investigation showed that the location of the transition is a measure of the disturbance level in the wind tunnel, and that the slender cone is a suitable model to indicate differences in disturbance level. Disturbances introduced in the subsonic portion of the tunnel appeared in measurable magnitude in the supersonic flow. A decreasing Reynolds number of transition was observed with increasing Mach number.


Descriptors :   *BOUNDARY LAYER TRANSITION , *SUPERSONIC FLOW , MACH NUMBER , SUPERSONIC WIND TUNNELS , LACQUERS , LUMINESCENCE , CONICAL BODIES , REYNOLDS NUMBER , SLENDER BODIES , ANGLES


Subject Categories : Fluid Mechanics


Distribution Statement : APPROVED FOR PUBLIC RELEASE